Ultra-large aperture remote sensing system and method based on space manufacturing and calculation reconstruction

Abstract

The invention discloses an ultra-large-diameter remote sensing system and method based on space manufacturing and calculation reconstruction. The ultra-large-diameter remote sensing system comprises a liquid primary mirror assembly, a secondary mirror, a secondary mirror truss, a rear-end optical module and a main load-bearing structure, the reflecting surface of the liquid primary mirror assembly is formed by injecting a liquid mirror material into a grid substrate structure of the liquid primary mirror assembly in a multi-point mode in an on-orbit mode and fusing the liquid mirror material and the grid substrate structure; the liquid primary mirror assembly is fixedly connected with the satellite platform through the main bearing structure; the secondary mirror truss is obtained through in-orbit 3D printing and is fixedly connected with the main force bearing structure; the secondary mirror is fixedly mounted on the secondary mirror truss; the secondary mirror receives a reflected light signal of the liquid primary mirror assembly and outputs the reflected light signal to the rear-end optical module; and the rear-end optical module is used for performing photoelectric conversion on the received optical signal and outputting image information. According to the invention, the engineering realization problem of the effective aperture of the large-aperture optical system is solved, and the development of a large-aperture space optical remote sensing system can be further promoted.

Description

Technical Field

[0001] This invention relates to the fields of space optical remote sensing and on-orbit manufacturing technology, and in particular to a method for realizing a mission-reconfigurable ultra-large aperture space optical remote sensing system based on fluid primary mirror dynamic shaping, on-orbit manufacturing of secondary mirror trusses, and computational adaptive optics correction. Background Technology

[0002] Large-aperture space optical remote sensing systems are crucial equipment for achieving high-resolution Earth observation and cutting-edge deep space exploration. Current space optical remote sensing systems generally employ rigid mirrors, but limitations imposed by existing material and manufacturing costs, launch vehicle fairing envelope size, and surface shape precision control technology make it difficult to deploy large-aperture systems exceeding 10 meters in orbit (the James Webb Space Telescope's largest primary mirror has a diameter of 6.5 meters, composed of 18 hexagonal modular mirrors).

[0003] By combining the on-orbit shaping technology of the fluid primary mirror under microgravity with the on-orbit manufacturing technology of the lightweight secondary mirror truss, and by manufacturing the optical system in an integrated manner on-orbit, it is expected to solve a series of bottleneck problems such as the limited launch volume of traditional solid mirrors, the complexity of the folding and unfolding mechanism, the reliance on heavy deformable mirrors for wavefront correction, and the irreversible thermal deformation caused by sudden temperature changes in the shadow region. This will enable the engineering on-orbit construction and deployment of ultra-large aperture optical remote sensing systems with apertures of 20m or more.

[0004] However, current on-orbit manufacturing only achieves meter-level antenna or bracket printing, and has not yet solved the problem of high-precision on-orbit manufacturing of ultra-large (hundred-meter-level) truss structures. Furthermore, maintaining the surface shape of ultra-large-diameter fluid mirrors under microgravity-thermal cycling remains problematic, and errors in mirror container unfolding and uneven liquid spreading will introduce residual aberrations of λ / 3 to λ / 5, leading to further degradation of image quality. Therefore, there is an urgent need for more feasible solutions for fluid primary mirror shaping, high-precision manufacturing of ultra-large secondary mirror trusses, and primary mirror surface shape control and image quality assurance. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of the existing technology and provide a system based on fluid dynamic shaping of the primary mirror and high-precision on-orbit manufacturing of the secondary mirror truss. This system breaks through the bottlenecks of the existing technology, solves the engineering realization problem of the effective aperture of optical systems larger than 20m, and can further promote the development of large-aperture space optical remote sensing systems.

[0006] This invention is achieved by the following technical solution: Firstly, A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped includes: a support frame, a grid substrate structure, a micro-pump and valve array, and distributed sensors; During launch, the support frame folds and collapses to form a cylindrical structure; when in orbit, the support frame unfolds to form a parabolic mesh structure. The supporting frame is a hollow structure, used as a flow channel for the fluid mirror material; The grid substrate structure is a flexible structural layer fixedly mounted on the support frame. The surface of the grid substrate structure is used for fluid mirror material injection, attachment and extension to form the mirror surface of the primary reflector. Miniature pump-valve arrays are used to control the flow rate of fluid mirrors; Distributed sensors are used to measure the positional deformation of the support frame and the thickness of the liquid film formed on the fluid mirror material on the grid substrate structure; The combination of a micro-pump valve array and distributed sensors enables the shaping and control of the reflector surface after on-orbit deployment.

[0007] Preferably, the support frame includes: a central hub, a main beam, and an annular adjusting beam; The central hub is used to drive the main beam to unfold and retract, and the central hub is fixedly connected to the main load-bearing structure. The main beam is connected to the adjusting beam, which is a ring structure with an adjustable circumference; multiple rings of adjusting beams are arranged radially along the parabolic structure network; the centers of the multiple rings of adjusting beams coincide. The parabolic curvature of the parabolic structure network can be adjusted by changing the perimeter of different adjustment beams. The main beam and the adjusting beam have hollow interiors, with the middle serving as a flow channel for the fluid mirror material.

[0008] Preferably, the main beam includes: a hinged truss and tension cables; During launch, the hinged truss folds and collapses to form a cylindrical structure; When in use on track, multiple hinged trusses intersect at a point to form a radial pattern, and the free ends of the hinged trusses are pre-tightened and locked by tension cables to form a parabolic structure network. The central hub is hinged to the main beam at the center of the parabolic structure net.

[0009] Preferably, the adjusting beam is made of shape memory alloy or is a lockable telescopic rod; The hinged truss is made of carbon fiber composite material.

[0010] Preferably, the grid substrate structure includes: a main support grid, a micro-adjustment point device, permeation holes, and edge dams; The main load-bearing grid is a flexible structural layer, and the main load-bearing grid is fixedly installed on the inner envelope surface of the adjusting beam to form a parabola; The micro-adjustment point device is fixedly installed on the main beam or the ring-shaped adjustment beam. Multiple micro-adjustment point devices are used in combination to adjust the surface accuracy of the parabolic surface formed by the main load-bearing grid. The main load-bearing grid has permeation holes machined at the intersection of the main beam and the adjustment beam. The permeation holes are used to allow the fluid mirror material to be injected, attached and extended to form the mirror surface of the main reflector. Edge dams are placed at the outer edge of the parabolic surface formed by the composite film array to prevent fluid mirror material from overflowing.

[0011] Preferably, the main load-bearing grid comprises: a composite membrane, an annular distributor, and radial branches; The composite membrane array is fixedly installed on the inner envelope surface of the adjusting beam to form a parabola; permeation holes are machined on the composite membrane at the intersection of the main beam and the adjusting beam; The composite film is a triangular film that can uniformly adsorb liquid mirror material through capillary force; Each triangular grid vertex of the composite membrane is defined as a micro-adjustment point; each micro-adjustment point is equipped with a micro-adjustment device. The annular distributor and radial branch pipe are fixedly installed on the adjusting beam. The annular distributor is used to guide the fluid mirror material transported from the adjusting beam through the radial branch pipe and the permeation hole in sequence, so that it adheres to the surface of the composite material membrane and extends to form the mirror surface of the main reflector.

[0012] Preferably, the micro pump valve array is fixedly installed on the radial branch pipe to control the flow rate within the radial branch pipe.

[0013] Preferably, the distributed sensors include: fiber optic grating sensors, laser interferometers, and thin-film sensors; Fiber Bragg grating sensors are used to measure the deformation of the main beam and the adjusting beam; A laser interferometer is used to measure the position of the substrate node formed by the intersection of the main beam and the adjustment beam; Thin-film sensors are used to monitor the thickness of liquid film formed on the surface of fluid mirror material in a grid substrate structure.

[0014] Secondly, A large-aperture remote sensing system based on space manufacturing and computational reconstruction includes: a secondary mirror, a secondary mirror truss, a rear optical module and a main load-bearing structure, and a liquid primary mirror assembly as described in the first aspect; The reflective surface of the liquid primary mirror assembly is formed by injecting liquid mirror material at multiple points on-orbit into the grid substrate structure of the liquid primary mirror assembly and fusing it; the liquid primary mirror assembly is fixedly connected to the satellite platform through the main load-bearing structure; The secondary mirror truss is obtained by 3D printing on track and is fixedly connected to the main load-bearing structure; The secondary mirror is fixedly mounted on the secondary mirror truss; the secondary mirror receives the reflected light signal from the liquid primary mirror assembly and outputs it to the back-end optical module; The back-end optical module is used to perform photoelectric conversion on the received light signals and output image information.

[0015] Thirdly, The method for implementing a space-based, computationally reconstructed, ultra-large aperture remote sensing system, as described in the second aspect, includes the following steps: 1) After launch and orbit insertion, the support frame area of ​​the liquid primary mirror assembly is kept within the operating temperature range by using the sunshade and light shield. The liquid primary mirror assembly is then deployed to form a parabolic structure mesh of the support frame, and the mesh substrate structure forms a parabolic surface on the inner envelope surface of the support frame. 2) Fiber optic grating sensors are used to measure the deformation of the main beam and the adjusting beam, and a laser interferometer is used to measure the position of the substrate node formed by the intersection of the main beam and the adjusting beam, so that the configuration of the support frame meets the design requirements. 3) The liquid mirror material in the storage tank on the control satellite platform is injected into the surface of the grid substrate structure through the main beam, adjusting beam, annular distributor and radial branch pipe in sequence, and it adheres and extends to form the mirror surface of the main reflector; after the liquid mirror surface extends and flattens, proceed to the next step; 4) The surface accuracy of the parabolic surface formed by the main bearing grid is adjusted by using a micro-adjustment point device, the liquid film thickness of the fluid mirror material on the surface of the grid substrate structure is monitored by using a thin film sensor, and the flow rate of the fluid mirror material is controlled by using a micro pump valve array, thereby dynamically shaping the main mirror surface to ensure surface accuracy. 5) On-orbit 3D printing of the secondary mirror truss, which enables the secondary mirror to be fixed to the main load-bearing structure, thus completing the remote sensing system implementation method.

[0016] Compared with the prior art, the advantages of the present invention are mainly reflected in the following aspects: 1) This invention can overcome the limitation of large aperture and realize the on-orbit deployment of optical remote sensing systems with an aperture of 20m or more; 2) This invention uses liquid mirror material and on-orbit dynamic shaping, which can ensure that the MTF after residual aberration correction is ≥0.35 (@50lp / mm). 3) The present invention adopts an integrated design of deployable truss structure and flexible structural layer for the ultra-large aperture primary mirror, which reduces the launch volume by 12:1 and reduces the launch cost by 40%. Attached Figure Description

[0017] Figure 1 Flowchart of the method of this invention.

[0018] Figure 2 Schematic diagram of an ultra-large aperture space optical remote sensing system; Figure 3 Schematic diagram of on-orbit deployment and shaping of the fluid primary mirror. Detailed Implementation

[0019] To better describe the present invention, the present invention will be described in detail below with reference to schematic diagrams and examples.

[0020] This invention employs a deployable, dynamically shaped liquid primary mirror assembly based on fluid mirror material. After on-orbit deployment, the liquid mirror material is synchronously injected from multiple points on the primary mirror frame (main beam and adjustment beam) onto the grid substrate structure of the liquid primary mirror assembly. Under the influence of microgravity and surface tension, the liquid mirror material fuses into a continuous and smooth reflective surface.

[0021] The ultra-large aperture remote sensing system comprises a liquid primary mirror assembly, a secondary mirror, a secondary mirror truss, a back-end optical module, and a main load-bearing structure. The reflective surface of the liquid primary mirror assembly is formed by injecting liquid mirror material at multiple points in orbit onto the lattice substrate structure of the liquid primary mirror assembly. The liquid primary mirror assembly is fixedly connected to the satellite platform via the main load-bearing structure. The secondary mirror truss is 3D printed in orbit and fixedly connected to the main load-bearing structure. The secondary mirror is fixedly mounted on the secondary mirror truss. The back-end optical module receives optical signals, performs photoelectric conversion, and outputs image information.

[0022] The liquid master mirror assembly includes: a support frame, a grid substrate structure, a micro-pump and valve array, and distributed sensors; The supporting frame is an expandable structure that forms a parabolic mesh after unfolding; the supporting frame is a hollow structure with the middle serving as a flow channel for the fluid mirror material. The grid substrate structure is a flexible structural layer fixedly installed on the support frame, used for the injection, attachment, and extension of fluid mirror material to form the mirror surface; the grid substrate structure is responsible for the attachment of the mirror material and provides a basis for fine-tuning the surface shape.

[0023] A micro-pump-valve array is used to control the flow rate of the fluid mirror material, and distributed sensors are used to measure the positional deformation of the support frame and the liquid film thickness of the fluid mirror material on the grid substrate structure. The combination of a micro-pump valve array and distributed sensors enables the shaping and control of the reflector surface after on-orbit deployment.

[0024] The supporting frame includes: a central hub, a main beam, and an annular adjustment beam; The center hub is used to drive the main beam to extend and retract, and the center hub is fixedly connected to the external load-bearing structure (such as...). Figure 2 (As shown).

[0025] The main beam comprises hinged trusses and tension cables; serving as the core load-bearing arm, similar to umbrella ribs, it employs a hybrid structure of "hinged trusses + tension cables." During launch, the trusses fold and retract like umbrella ribs to form a cylindrical structure; during deployment, multiple hinged trusses intersect at a point to form a radial pattern, with the free ends of the hinged trusses pre-tensioned and locked by tension cables, forming a structural network with a parabolic inner envelope. The hinged trusses are made of carbon fiber composite material, with a locking force ≥10 kN, ensuring controllable impact.

[0026] The central hub is hinged to the main beam at the center of the parabolic structure net; The adjusting beam is a ring structure with an adjustable circumference; multiple rings of adjusting beams are arranged radially along the parabolic structural network; the centers of the multiple rings of adjusting beams coincide; such as... Figure 3 As shown.

[0027] The parabolic curvature of the parabolic structure network can be adjusted by changing the perimeter of different adjustment beams, with a curvature positioning accuracy of ≤0.1 mm.

[0028] The adjusting beam is made of shape memory alloy or designed as a lockable telescopic rod.

[0029] The main beam is connected to the adjusting beam.

[0030] The main beam and the adjusting beam have hollow interiors, with the middle serving as a flow channel for the fluid mirror material.

[0031] The grid substrate structure includes: a main support grid, micro-adjustment point devices, permeation holes, and edge dams; The main load-bearing grid is a flexible structural layer, and the main load-bearing grid is fixedly installed on the inner envelope surface of the adjusting beam to form a parabola; The main load-bearing grid consists of: a composite membrane, a ring distributor, and radial branches; The composite material film array is fixedly installed on the inner envelope surface of the adjusting beam to form a parabola; the composite material film is a triangular hydrophilic ceramic film or polymer film, which can uniformly adsorb liquid mirror material through capillary force.

[0032] The composite membrane has permeation holes machined at the intersection of the main beam and the adjusting beam; The annular distributor and radial branch pipe are fixedly installed on the adjusting beam. The annular distributor is used to guide the fluid mirror material transported from the adjusting beam through the radial branch pipe and the permeation hole in sequence, so that it adheres to the surface of the composite material membrane and extends to form the mirror surface of the main reflector.

[0033] The micro-adjustment point device is fixedly installed on the main beam or the ring adjustment beam. Multiple micro-adjustment point devices are used in combination to adjust the surface accuracy of the parabolic surface formed by the composite material membrane array. Each triangular mesh vertex of the composite membrane is defined as a micro-adjustment point. Each micro-adjustment point is equipped with a micro-adjustment device. The micro-adjustment point device is implemented using an actuator, that is, a three-degree-of-freedom (XYZ) piezoelectric ceramic or magnetostrictive actuator is installed at each micro-adjustment point, with a stroke of ±100 μm and a resolution of ≤10 nm. It is the key actuator to achieve λ / 20 surface accuracy.

[0034] An edge dam is positioned at the outer edge of the parabolic surface formed by the composite film array to prevent fluid from overflowing. The edge dam is an annular silicone sealing ring.

[0035] The miniature pump-valve array is fixedly installed on the radial branch pipe to control the flow rate within the radial branch pipe, enabling global injection and local fine-tuning of the liquid mirror material.

[0036] Distributed sensors include: fiber Bragg grating sensors, laser interferometers, and thin-film sensors; Fiber optic grating sensors are used to measure the deformation of the main beam and the adjusting beam frame; A laser interferometer is used to measure the position of the substrate node formed by the intersection of the main beam and the adjustment beam; Thin-film sensors are used to monitor the thickness of liquid film formed on the surface of fluid mirror material in a grid substrate structure.

[0037] The liquid mirror material in the storage tank is injected into the surface of the grid substrate structure through the main beam, adjusting beam, annular distributor, and radial branch pipe in sequence.

[0038] A method for implementing an ultra-large aperture remote sensing system based on space manufacturing and computational reconstruction, comprising the following steps: 1) After launch and orbit insertion, the support frame area of ​​the liquid primary mirror assembly is kept within the operating temperature range by using the sunshade and light shield. The liquid primary mirror assembly is then deployed to form a parabolic structure mesh of the support frame, and the mesh substrate structure forms a parabolic surface on the inner envelope surface of the support frame. 2) Fiber optic grating sensors are used to measure the deformation of the main beam and the adjusting beam, and a laser interferometer is used to measure the position of the substrate node formed by the intersection of the main beam and the adjusting beam, so that the configuration of the support frame meets the design requirements. 3) The liquid mirror material in the storage tank on the control satellite platform is injected into the surface of the grid substrate structure through the main beam, adjusting beam, annular distributor and radial branch pipe in sequence, and it adheres and extends to form the mirror surface of the main reflector; after the liquid mirror surface extends and flattens, proceed to the next step; 4) The surface accuracy of the parabolic surface formed by the main bearing grid is adjusted by using a micro-adjustment point device, the liquid film thickness of the fluid mirror material on the surface of the grid substrate structure is monitored by using a thin film sensor, and the flow rate of the fluid mirror material is controlled by using a micro pump valve array, thereby dynamically shaping the main mirror surface to ensure surface accuracy. 5) On-orbit 3D printing of the secondary mirror truss, which enables the secondary mirror to be fixed to the main load-bearing structure, thus completing the remote sensing system implementation method.

[0039] Example This invention provides a method for realizing a mission-reconfigurable ultra-large aperture space optical remote sensing system based on fluidic primary mirror dynamic shaping, on-orbit manufacturing of secondary mirror trusses, and computational adaptive optics correction. Figure 1 As shown, it includes the following steps: Step S100: High compression ratio launch. The system adopts an integrated platform and load design, placing the fluid primary mirror feeding and control system and the secondary mirror truss 3D printing system in the main load-bearing structure of the system load module. The primary mirror frame, sunshade, and solar array are folded and fixed to the outside of the load-bearing module with a compression ratio of 12:1 or higher, forming a launch envelope with a diameter ≤5m and a height ≤10m (20m caliber system). Step S200, on-orbit deployment and locking: After launch into orbit, the system deploys the solar array to provide power and deploys the sunshade and light shield to keep the primary mirror frame within a suitable temperature range. Then, the parabolic grid substrate structure of the liquid primary mirror assembly is deployed. Its deployment accuracy is fed back by the laser rangefinder and controlled by the servo mechanism, with a point position error ≤0.1mm. A shape memory alloy intelligent locking device is then used to provide kN-level locking force and low-impact release. Step S300: Dynamic shaping of the fluid primary mirror. The primary mirror feeding and control system synchronously injects liquid mirror material from multiple points on the primary mirror frame (main beam and adjustment beam) onto the grid substrate structure. Under the influence of microgravity and surface tension, the liquid mirror material fuses into a continuous and smooth reflective surface. After the liquid mirror surface stretches and flattens, the control system performs active surface shape control and continues to dynamically shape the primary mirror to ensure that the surface shape accuracy is better than λ / 20 (RMS). In step S300, the primary mirror material supply is divided into a global injection and a local fine-tuning process. Global injection refers to the supply system directly injecting a predetermined amount of liquid mirror material according to the mirror model; local fine-tuning takes into account the evaporation and non-ideal distribution of the liquid mirror material. In step S300, the active surface control system may take the following forms, including but not limited to: 1. a substrate grid fine-tuning servo mechanism; 2. a substrate grid active temperature control system; 3. a substrate grid electromagnetic force control system using ferromagnetic liquid mirror material.

[0040] Step S400: On-orbit 3D printing of the secondary mirror truss. The secondary mirror truss 3D printing system, which is built into the main load-bearing module, is connected to the secondary mirror foundation through a lifting mechanism. The main body of the secondary mirror truss is printed on-orbit using continuous fiber-reinforced thermoplastic composite material. The secondary mirror is sent to the predetermined position by truss additive lifting. The printing accuracy of the truss is controlled by real-time structured light 3D vision measurement feedback to ensure that the printing error is ≤50μm. In step S400, the 3D printer needs to use a continuous fiber co-extrusion nozzle with a fiber volume fraction of 55%, a print layer thickness of 0.1 mm, and a printing speed of 20 mm / s.

[0041] Step S500: Calculate adaptive optics to eliminate residual aberrations. The system uses a combination of adaptive optics hardware real-time wavefront correction and computational optics "physical modeling + algorithm compensation" to eliminate residual aberrations. The wavefront sensor acquires the primary mirror-secondary mirror wavefront in real time, and the deformation monitoring data of the primary mirror and truss are acquired through the on-orbit manufacturing system. The on-board AI processor generates digital phase conjugate surface shape, drives the dynamic shaping of the primary mirror, and uses post-processing algorithms to eliminate residual aberrations. After correction, the wavefront error is ≤λ / 50 (RMS). In step S500, the AI ​​processor is an FPGA-GPU heterogeneous architecture with a peak computing power of over 5 TFLOPS and a power consumption of less than 50W.

[0042] Step S600: Task adaptive reconstruction. Based on the requirements of the remote sensing mission, the surface shape focal length is changed by active surface shape control of the liquid primary mirror, or the optical filtering function is switched to achieve seamless conversion between high-resolution panchromatic mode and wide field-of-view multispectral mode.

[0043] It should be understood that the specific embodiments described above are merely illustrative or explanatory of the principles of the invention and do not constitute a limitation thereof. Therefore, any modifications, equivalent substitutions, improvements, etc., made without departing from the spirit and scope of the invention should be included within the protection scope of the invention. Furthermore, the appended claims are intended to cover all variations and modifications falling within the scope and boundaries of the appended claims, or equivalent forms of such scope and boundaries.

[0044] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any person skilled in the art can make possible variations and modifications to the technical solutions of the present invention using the disclosed methods and techniques without departing from the spirit and scope of the 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 present invention. Where there is no conflict, the embodiments of this application and the technical features thereof can be combined with each other.

[0045] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped, characterized in that, include: Support framework, grid substrate structure, micro-pump valve array, and distributed sensors; During launch, the support frame folds and retracts to form a cylindrical structure; When in orbit, the support frame unfolds to form a parabolic structure network; The supporting frame is a hollow structure, used as a flow channel for the fluid mirror material; The grid substrate structure is a flexible structural layer fixedly mounted on the support frame. The surface of the grid substrate structure is used for fluid mirror material injection, attachment and extension to form the mirror surface of the primary reflector. Miniature pump-valve arrays are used to control the flow rate of fluid mirrors; Distributed sensors are used to measure the positional deformation of the support frame and the thickness of the liquid film formed on the fluid mirror material on the grid substrate structure; The combination of a micro-pump valve array and distributed sensors enables the shaping and control of the reflector surface after on-orbit deployment.

2. The liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped according to claim 1, characterized in that, The supporting frame includes: a central hub, a main beam, and an annular adjustment beam; The central hub is used to drive the main beam to unfold and retract, and the central hub is fixedly connected to the main load-bearing structure. The main beam is connected to the adjusting beam, which is a ring structure with an adjustable circumference; multiple rings of adjusting beams are arranged radially along the parabolic structure network; the centers of the multiple rings of adjusting beams coincide. The parabolic curvature of the parabolic structure network can be adjusted by changing the perimeter of different adjustment beams. The main beam and the adjusting beam have hollow interiors, with the middle serving as a flow channel for the fluid mirror material.

3. A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped according to claim 2, characterized in that, The main beam includes: hinged trusses and tension cables; During launch, the hinged truss folds and collapses to form a cylindrical structure; When in use on track, multiple hinged trusses intersect at a point to form a radial pattern, and the free ends of the hinged trusses are pre-tightened and locked by tension cables to form a parabolic structure network. The central hub is hinged to the main beam at the center of the parabolic structure net.

4. A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped according to claim 3, characterized in that, The adjusting beam is made of shape memory alloy or a lockable telescopic rod; The hinged truss is made of carbon fiber composite material.

5. A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped according to any one of claims 2-4, characterized in that, The grid substrate structure includes: a main support grid, micro-adjustment point devices, permeation holes, and edge dams; The main load-bearing grid is a flexible structural layer, and the main load-bearing grid is fixedly installed on the inner envelope surface of the adjusting beam to form a parabola; The micro-adjustment point device is fixedly installed on the main beam or the ring-shaped adjustment beam. Multiple micro-adjustment point devices are used in combination to adjust the surface accuracy of the parabolic surface formed by the main load-bearing grid. The main load-bearing grid has permeation holes machined at the intersection of the main beam and the adjustment beam. The permeation holes are used to allow the fluid mirror material to be injected, attached and extended to form the mirror surface of the main reflector. Edge dams are placed at the outer edge of the parabolic surface formed by the composite film array to prevent fluid mirror material from overflowing.

6. A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped according to claim 5, characterized in that, The main load-bearing grid consists of: a composite membrane, a ring distributor, and radial branches; The composite membrane array is fixedly installed on the inner envelope surface of the adjusting beam to form a parabola; permeation holes are machined on the composite membrane at the intersection of the main beam and the adjusting beam; The composite film is a triangular film that can uniformly adsorb liquid mirror material through capillary force; Each triangular grid vertex of the composite membrane is defined as a micro-adjustment point; each micro-adjustment point is equipped with a micro-adjustment device. The annular distributor and radial branch pipe are fixedly installed on the adjusting beam. The annular distributor is used to guide the fluid mirror material transported from the adjusting beam through the radial branch pipe and the permeation hole in sequence, so that it adheres to the surface of the composite material membrane and extends to form the mirror surface of the main reflector.

7. A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped according to claim 6, characterized in that, The miniature pump valve array is fixedly installed on the radial branch pipe to control the flow rate within the radial branch pipe.

8. A liquid primary mirror assembly based on a fluid mirror material that can be unfolded and shaped according to claim 7, characterized in that, Distributed sensors include: fiber Bragg grating sensors, laser interferometers, and thin-film sensors; Fiber Bragg grating sensors are used to measure the deformation of the main beam and the adjusting beam; A laser interferometer is used to measure the position of the substrate node formed by the intersection of the main beam and the adjustment beam; Thin-film sensors are used to monitor the thickness of liquid film formed on the surface of fluid mirror material in a grid substrate structure.

9. A large-aperture remote sensing system based on space manufacturing and computational reconstruction, characterized in that, include: The secondary mirror, secondary mirror truss, rear optical module and main load-bearing structure, and the liquid primary mirror assembly as described in claim 8; The reflective surface of the liquid primary mirror assembly is formed by injecting liquid mirror material at multiple points on-orbit into the grid substrate structure of the liquid primary mirror assembly and fusing it; the liquid primary mirror assembly is fixedly connected to the satellite platform through the main load-bearing structure; The secondary mirror truss is obtained by 3D printing on track and is fixedly connected to the main load-bearing structure; The secondary mirror is fixedly mounted on the secondary mirror truss; the secondary mirror receives the reflected light signal from the liquid primary mirror assembly and outputs it to the back-end optical module; The back-end optical module is used to perform photoelectric conversion on the received light signals and output image information.

10. A method for implementing an ultra-large aperture remote sensing system based on space manufacturing and computational reconstruction, applicable to the ultra-large aperture remote sensing system based on space manufacturing and computational reconstruction as described in claim 9, characterized in that... Including the following steps: 1) After launch and orbit insertion, the support frame area of ​​the liquid primary mirror assembly is kept within the operating temperature range by using the sunshade and light shield. The liquid primary mirror assembly is then deployed to form a parabolic structure mesh of the support frame, and the mesh substrate structure forms a parabolic surface on the inner envelope surface of the support frame. 2) Fiber optic grating sensors are used to measure the deformation of the main beam and the adjusting beam, and a laser interferometer is used to measure the position of the substrate node formed by the intersection of the main beam and the adjusting beam, so that the configuration of the support frame meets the design requirements. 3) The liquid mirror material in the storage tank on the control satellite platform is injected into the surface of the grid substrate structure through the main beam, adjusting beam, annular distributor and radial branch pipe in sequence, and it adheres and extends to form the mirror surface of the main reflector; after the liquid mirror surface extends and flattens, proceed to the next step; 4) The surface accuracy of the parabolic surface formed by the main bearing grid is adjusted by using a micro-adjustment point device, the liquid film thickness of the fluid mirror material on the surface of the grid substrate structure is monitored by using a thin film sensor, and the flow rate of the fluid mirror material is controlled by using a micro pump valve array, thereby dynamically shaping the main mirror surface to ensure surface accuracy. 5) On-orbit 3D printing of the secondary mirror truss, which enables the secondary mirror to be fixed to the main load-bearing structure, thus completing the remote sensing system implementation method.

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