Space large aperture optical satellite capable of on-orbit assembly

Abstract

The application provides a space large-aperture optical satellite capable of on-orbit assembly, which relates to the technical field of satellite overall design, and comprises a solar cell array, a cell module, an expandable sunshade, a multi-arm robot, an optical post-processing module and a sub-reflector, the optical post-processing module is connected to the cell module, the cell module and the expandable sunshade are respectively connected to the mechanical arm of the multi-arm robot, and the solar cell array and the sub-reflector are respectively connected to the outside of the multi-arm robot; the space large-aperture optical satellite is switched between on-orbit assembly and layering and compacting launch in space. The layering and compacting launch scheme provided by the application can realize the on-orbit assembly of the space large-aperture optical satellite in a single launch under the existing carrier fairing envelope, and has the characteristics of high efficiency, large combined rigidity, high imaging quality and wide application range; the cell module adopts a "5-6-6" type platform configuration, and has the characteristics of space symmetry, high replaceability, good repeatability and good space stability.

Description

Technical Field

[0001] This invention relates to the field of satellite overall design technology, and more specifically, to a large-aperture optical satellite that can be assembled in orbit. Background Technology

[0002] The development of optical remote sensing satellites is moving towards higher operational efficiency, including wider swaths, higher resolution, and higher sensitivity. Increased resolution means larger optical system apertures, but this is limited by current technology, manufacturing costs, launch vehicle thrust, and launch vehicle fairing envelope. Traditional solutions using a single, solid primary mirror are no longer sufficient. On-orbit assembly (OOR) is a technology that sequentially assembles functional components from single or multiple launches into a desired configuration. This system consists of the assembly object, assembly tools, and an assembly platform (if necessary). It can be used to assemble two or more independent spacecraft into larger space structures, dock and assemble modules or sections to create a single spacecraft, expand or reconfigure its functionality, or assemble modules and components into new payload modules. OOR technology features high structural efficiency, strong scalability, and the ability to be progressively upgraded, making it an important direction for the development of large-aperture optical remote sensing satellites.

[0003] A search of existing technologies revealed that various on-orbit assembled optical payload concepts have been proposed abroad, but none have disclosed feasible research schemes or pathways. Chinese invention patent application 201110237143.0 discloses a foldable, launchable, and easily assembled on-orbit truss unit. This truss unit consists of four columns, four transverse support rods, four longitudinal support rods, and two inclined tubes. The columns and support rods are made of an inflatable, deployable, and rigid material. The truss unit uses an inflation pressure-driven deployment method. However, this on-orbit assembled truss unit is suitable for on-orbit assembly of truss-type satellites, but its combined stiffness is relatively low, failing to meet the development requirements of high-precision, large-aperture optical remote sensing satellites, thus limiting its applicability. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the purpose of this invention is to provide a large-aperture optical satellite that can be assembled in orbit. The overall design of this invention solves the problem of maximizing the aperture of the optical satellite payload within the existing launch vehicle fairing envelope. It adopts an integrated camera platform satellite configuration design, which features high assembly rigidity, high imaging quality, and wide applicability.

[0005] According to the present invention, a space-based large-aperture optical satellite that can be assembled in orbit includes a solar array, a cell module, a deployable sunshade, a multi-arm robot, an optical post-processing module, and a sub-reflector. The optical post-processing module is connected to the cell module, and the cell module and the deployable sunshade are respectively connected to the robotic arm of the multi-arm robot. The solar array and the sub-reflector are respectively connected to the outside of the multi-arm robot. The space-based large-aperture optical satellite can switch between in-orbit assembly in space and stacked compaction launch.

[0006] Preferably, when in the stacked and compressed launch mode, the solar array, cell module, deployable sunshade, optical post-processing module, and sub-reflector are connected to the launch vehicle via a multi-arm robot.

[0007] Preferably, the multi-arm robot includes a vision control system and robotic arms, with multiple robotic arms respectively connected to the vision control system;

[0008] When in the space-based on-orbit assembly mode, the multi-arm robot uses a vision control system to identify the basic assembly structure, enabling multiple robotic arms to grasp, coordinate and control, and assemble the basic structures on-orbit.

[0009] Preferably, the robotic arm and the cell module are connected in a one-to-one correspondence.

[0010] Preferably, the robotic arm has seven degrees of freedom and three working modes: "one leg and three hands", "two legs and two hands", and "three legs and one hand".

[0011] Preferably, the cell module adopts a "5-6-6" platform configuration module. The cell module includes a regular pentagon module and two regular hexagon modules. The two regular hexagon modules are respectively connected to the two adjacent sides of the regular pentagon module, and the two regular hexagon modules are interconnected.

[0012] Preferably, the regular pentagonal module and the regular hexagonal module have the same structure, including a regular polygonal structure platform, an actuator, a system module unit and an optical lens. The regular polygonal structure platform is connected to the system module unit, and the upper part of the regular polygonal structure platform is connected to the optical lens through the actuator.

[0013] The actuator performs on-orbit error adaptive adjustment of the optical lens based on the calculated optical lens deformation error to ensure high imaging quality.

[0014] Preferably, the optical lens is equipped with an optical measurement system, which measures the position and relative position of the optical lens and calculates the deformation error of the optical lens.

[0015] Preferably, the deployable light shield is deployed in the space-orbit assembly state and retracted in the stacked and compressed launch state.

[0016] An expandable sunshade isolates stray light.

[0017] Preferably, the solar cell array has multiple solar cells attached to it, and the solar cell array converts solar energy into electrical energy.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] (1) The stacked and compacted launch scheme proposed in this invention can realize the on-orbit assembly of large-aperture optical satellites in a single launch under the existing launch fairing envelope, which has the characteristics of high efficiency.

[0020] (2) The present invention adopts a “5-6-6” platform configuration cell module, which has the characteristics of spatial symmetry, high substitutability, good repeatability and good spatial stability.

[0021] (3) The integrated satellite configuration of the camera platform of the present invention has stronger structural rigidity, and the actuator can realize on-orbit error adaptive adjustment of optical lenses, and has the characteristics of high on-orbit surface accuracy.

[0022] (4) The stacked compression launch and on-orbit assembly scheme of the present invention can also be extended to the development of other spacecraft, and has the characteristics of wide applicability. Attached Figure Description

[0023] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0024] Figure 1 This is a schematic diagram of the overall satellite configuration after on-orbit assembly according to the present invention;

[0025] Figure 2 This is a schematic diagram of the stacked compression launch scheme of the present invention;

[0026] Figure 3 This is a schematic diagram of the "5-6-6" configuration cell module of the present invention;

[0027] Figure 4 This is a schematic diagram of a single regular polygonal module of the present invention;

[0028] Figure 5 This is a schematic diagram of the on-orbit assembly method of the multi-arm robot of the present invention.

[0029] The diagram is labeled as follows: 1. Solar cell array; 2. Cell module; 21. Regular polygon module; 211. Regular polygon structure platform; 212. Actuator; 213. System module unit; 214. Optical lens; 215. Optical measurement system; 22. Regular hexagon module; 3. Deployable sunshade; 4. Multi-arm robot; 41. Vision control system; 42. Robotic arm; 5. Optical post-processing module; 6. Sub-reflector. Detailed Implementation

[0030] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0031] Example

[0032] According to the present invention, a large-aperture optical satellite that can be assembled in orbit is provided, such as Figure 1-5 As shown, the satellite employs a stacked, compressed launch and on-orbit assembly method. Its basic structure includes a solar array 1, a cell module 2, a deployable sunshade 3, a multi-arm robot 4, an optical post-processing module 5, and a sub-reflector 6. The optical post-processing module 5 is connected to the cell module 2. The cell module 2 and the deployable sunshade 3 are respectively connected to the robotic arms 42 of the multi-arm robot 4. The solar array 1 and the sub-reflector 6 are respectively connected to the outside of the multi-arm robot 4. Multiple solar cells are attached to the solar array 1, which converts solar energy into electrical energy to power the satellite. The deployable sunshade 3 deploys during on-orbit assembly and retracts during the stacked, compressed launch state; the deployable sunshade 3 isolates stray light from the optical camera.

[0033] In the stacked and compressed launch mode, the solar array 1, cell module 2, deployable sunshade 3, optical post-processing module 5, and sub-reflector 6 are connected to the launch vehicle via a multi-arm robot 4. The multi-arm robot 4 includes a vision control system 41 and robotic arms 42, with multiple robotic arms 42 connected to the vision control system 41. In the on-orbit assembly mode, the multi-arm robot 4 uses the vision control system 41 to identify the basic assembly structure, enabling the multiple robotic arms 42 to grasp, coordinate, and assemble the basic structures in orbit. Each robotic arm 42 has seven degrees of freedom and operates in three modes: "one leg and three arms," ​​"two legs and two arms," ​​and "three legs and one arm." Each robotic arm 42 is connected to a cell module 2 in a one-to-one correspondence.

[0034] Cell module 2 adopts a "5-6-6" platform configuration. Cell module 2 includes one regular pentagonal module 21 and two regular hexagonal modules 22. The two regular hexagonal modules 22 are respectively connected to the two adjacent sides of the regular pentagonal module 21, and the two regular hexagonal modules 22 are interconnected. The regular pentagonal module 21 and the regular hexagonal module 22 have the same structure, including a regular polygonal structure platform 211, an actuator 212, a system module unit 213, an optical lens 214, and an optical measurement system 215. The regular polygonal structure platform 211 is connected to the system module unit 213, and the upper side of the regular polygonal structure platform 211 is connected to the optical lens 214 through the actuator 212. The actuator 212 performs on-orbit error adaptive adjustment of the optical lens 214 based on the calculated deformation error of the optical lens 214 to ensure high imaging quality. An optical measurement system 215 is provided on the optical lens 214. The optical measurement system 215 measures the position and relative position of the optical lens 214 and calculates the deformation error of the optical lens 214. Preferably, the actuator 212 is a piezoelectric actuator and the optical measurement system 215 is a six-degree-of-freedom laser measurement system.

[0035] More specifically, the stacked and compacted launch scheme proposed in this invention can achieve on-orbit assembly of large-aperture optical satellites in a single launch within the existing launch vehicle fairing envelope, characterized by high efficiency. The cell module 2, employing three regular polygonal modules, possesses higher structural rigidity, and the satellite assembly configuration exhibits spatial symmetry, high substitutability, good repeatability, and good space stability. On-orbit error measurement and adaptive calibration of the optical lenses are achieved through optical measurement devices and actuators, ensuring the on-orbit surface accuracy of the optical lenses and resulting in high imaging quality. This stacked and compacted launch and on-orbit assembly scheme can also be extended to the development of other spacecraft, demonstrating its wide applicability.

[0036] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0037] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A large-aperture optical satellite that can be assembled in orbit, characterized in that, The system includes a solar cell array (1), a cell module (2), a deployable sunshade (3), a multi-arm robot (4), an optical post-processing module (5), and a sub-reflector (6). The optical post-processing module (5) is connected to the cell module (2). The cell module (2) and the deployable sunshade (3) are respectively connected to the robotic arm (42) of the multi-arm robot (4). The solar cell array (1) and the sub-reflector (6) are respectively connected to the outside of the multi-arm robot (4). The space large-aperture optical satellite switches between on-orbit assembly in space and stacked compaction launch. The cell module (2) adopts a "5-6-6" platform configuration module. The cell module (2) includes a regular pentagon module (21) and two regular hexagon modules (22). The two regular hexagon modules (22) are respectively connected to the two adjacent sides of the regular pentagon module (21), and the two regular hexagon modules (22) are interconnected. The regular pentagonal module (21) and the regular hexagonal module (22) have the same structure, including a regular polygonal structure platform (211), an actuator (212), a system module unit (213), and an optical lens (214). The regular polygonal structure platform (211) is connected to the system module unit (213), and the upper side of the regular polygonal structure platform (211) is connected to the optical lens (214) through the actuator (212). The actuator (212) performs on-orbit error adaptive adjustment of the optical lens (214) based on the calculated deformation error of the optical lens (214) to ensure high imaging quality.

2. The space-based large-aperture optical satellite that can be assembled in orbit according to claim 1, characterized in that, When in the stacked and compressed launch mode, the solar cell array (1), the cell module (2), the deployable sunshade (3), the optical post-processing module (5), and the sub-reflector (6) are connected to the launch vehicle through the multi-arm robot (4).

3. The space-based large-aperture optical satellite that can be assembled in orbit according to claim 1, characterized in that, The multi-arm robot (4) includes a vision control system (41) and robotic arms (42), with multiple robotic arms (42) respectively connected to the vision control system (41); When in the space on-orbit assembly mode, the multi-arm robot (4) completes the identification of the basic assembly structure through the vision control system (41), and realizes the grasping, coordinated control and on-orbit assembly of the multiple robotic arms (42) and each basic structure.

4. The space-based large-aperture optical satellite that can be assembled in orbit according to claim 3, characterized in that, The robotic arm (42) is connected to the cell module (2) in a one-to-one correspondence.

5. The space-based large-aperture optical satellite that can be assembled in orbit according to claim 3, characterized in that, The robotic arm (42) has seven degrees of freedom and three working modes: "one leg and three hands", "two legs and two hands" and "three legs and one hand".

6. The space-based large-aperture optical satellite that can be assembled in orbit according to claim 1, characterized in that, An optical measurement system (215) is provided on the optical lens (214). The optical measurement system (215) measures the pose and relative pose of the optical lens (214) and calculates the deformation error of the optical lens (214).

7. The space-based large-aperture optical satellite that can be assembled in orbit according to claim 1, characterized in that, The deployable light shield (3) is deployed in the space on-orbit assembly state and retracted in the stacked and compressed emission state. The deployable light shield (3) isolates stray light.

8. The space-based large-aperture optical satellite that can be assembled in orbit according to claim 1, characterized in that, The solar cell array (1) has multiple solar cells attached to it, and the solar cell array (1) converts solar energy into electrical energy.

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