Gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device

Abstract

The invention provides a gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device which comprises a solar wing and antenna integrated mechanism and a pressing and releasing mechanism which are symmetrically arranged on the four sides of a micro-nano satellite body, and the solar wing and antenna integrated mechanism comprises an outer plate, an inner plate and a hinge locking mechanism; the hinge locking mechanisms are arranged between the outer plate and the inner plate and between the inner plate and the star body, the inner plate and the outer plate are locked on the star body by the pressing and releasing mechanism in a folded state, and the patch surface of the inner plate faces the outside; after the satellite solar wing enters an orbit, the pressing and releasing mechanism is unlocked, the inner plate and the outer plate are unfolded, and the satellite solar wing is in a cross shape. Through three innovations of materials, structures and functions, the inherent contradiction of discrete design of micro-nano satellite energy and a communication system is solved, breakthrough is achieved in the dimensions of size, cost, reliability and the like, and definite engineering landing value and market competitiveness are achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite management equipment, and in particular to a gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device. Background Art

[0002] With the rapid development of micro-nano satellite technology, micro-nano satellites weighing ≤100kg are lightweight, easy to transport, and highly economical. With the rapid advancement of microelectronics and micromechanics, their utility is gradually increasing. Traditional micro-nano satellites, with separate solar panels and communication antennas, suffer from drawbacks such as low space utilization, heavy weight, and complex operation. Furthermore, to provide sufficient energy for the satellite, the solar panels must be large enough. Larger satellite antennas also enable the miniaturization of ground antennas. Integrating common features between solar panels and antennas offers significant practical value and innovation. Summary of the Invention

[0003] In view of the defects in the prior art, the present invention provides a gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device to solve the problems in the above-mentioned background technology.

[0004] The present invention provides a gradient thermal compensation micro-nano satellite solar wing and antenna integration device, comprising a solar wing and antenna integration mechanism and a compression and release mechanism symmetrically arranged on the four sides of the micro-nano satellite body, the solar wing and antenna integration mechanism comprising an outer panel, an inner panel and a hinge locking mechanism; the hinge locking mechanism is arranged between the outer panel and the inner panel, and between the inner panel and the satellite body; when the compression and release mechanism is in a retracted state, it locks the inner panel and the outer panel on the satellite body, with the patch surface of the inner panel facing outward; after the satellite solar wing enters orbit, the compression and release mechanism is unlocked, the inner panel and the outer panel are unfolded, and the satellite solar wing forms a "cross" shape.

[0005] Preferably, the inner panel and the outer panel respectively include an ultra-thin flexible photovoltaic layer, a thermal-electrical-mechanical coupling isolation module and an S-band conformal antenna arranged from top to bottom.

[0006] Preferably, the ultra-thin flexible photovoltaic layer comprises: a solar cell sheet and a solar wing substrate; The solar cell is a gallium arsenide rigid cell; The solar wing substrate is a carbon fiber reinforced polyimide substrate; The copper microstrip line is laser-etched on the back of the polyimide film between the solar cell and the solar wing substrate, and the MPPT control circuit is integrated.

[0007] Preferably, the solar wing substrate includes carbon fiber cross grids arranged on the upper and lower surfaces and aluminum honeycombs arranged between the carbon fiber cross grids.

[0008] Preferably, the thermal-electrical-mechanical coupling isolation module comprises an aluminum silicon carbide honeycomb panel, a silicon dioxide aerogel layer, a graphene directional heat conducting film, a polyimide insulating layer, and a functionally gradient alloy layer; The aluminum silicon carbide honeycomb panel is used for efficient heat dissipation and for supporting the ultra-thin flexible photovoltaic layer; The silica aerogel layer is used to block heat conduction and reduce the temperature gradient between layers; The graphene directional heat-conducting film is used to directionally conduct heat from local hot spots; The polyimide insulation layer is used for electrical isolation and reduces electromagnetic coupling loss; The functionally gradient alloy layer is used to match the thermal expansion of the upper and lower layers and suppress interface stress.

[0009] Preferably, the functionally gradient alloy layer is composed of a Ti / SiC composite material, and the thermal expansion coefficient can be gradually changed.

[0010] Preferably, the S-band conformal antenna includes a serpentine routing radiation patch, a dielectric substrate, and a metal feed post.

[0011] Preferably, the hinge locking mechanism adopts a biaxial folding hinge, integrating an SMA wire-driven pre-tightening mechanism and a mechanical ratchet locking mechanism.

[0012] Preferably, the radiating patch of the S-band conformal antenna is fed through H-shaped slot coupling, an ultra-thin copper layer is deposited on the back of the substrate by a magnetron sputtering process, and the H-shaped slot is formed by photolithography; the length of the radiating patch of the S-band conformal antenna is 0.48 times the operating wavelength (λ), satisfying the relationship: Where c is the speed of light, f is the center frequency of the antenna, and εr is the dielectric constant of the substrate; The transverse length and wavelength of the H-shaped gap satisfy: Ws=0.12λ The longitudinal length meets the following requirements: Ls=0.25λ Preferably, the S-band conformal antenna is a wave number synthesis array antenna comprising 5×4 radiating patch units, with a spacing of 0.8λ between adjacent units; Each unit adjusts the phase difference Δφ through the phase shifter to meet the wave number synthesis condition: Where k = 2π / λ is the wave number, d = 0.8λ is the unit spacing, and θ is the beam pointing angle.

[0013] Beneficial effects of the present invention The present invention provides a gradient thermal compensation micro-nano satellite solar wing and antenna integrated device. Through triple innovation in materials, structure and function, it solves the inherent contradiction in the discrete design of micro-nano satellite energy and communication systems, achieves breakthroughs in dimensions such as volume, cost and reliability, and has clear engineering implementation value and market competitiveness. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of the antenna structure in the deployed state of the present invention; Figure 2 This is a schematic diagram of the solar wing structure of the present invention in the expanded state; Figure 3 It is a schematic diagram of the structure of the present invention in a contracted state; Figure 4 Schematic diagram of the cross-sectional structure of the thermal-electrical-mechanical coupling isolation module of the present invention; Among them, 1. Inner panel; 2. Outer panel; 3. Hinge locking mechanism; 5. Compression release mechanism; 100. Ultra-thin flexible photovoltaic layer; 110. Solar cell sheet; 120. Solar wing substrate; 200. Thermal-electrical-mechanical coupling isolation module; 210. Aluminum silicon carbide honeycomb panel; 220. Silica aerogel layer; 230. Graphene directional heat conduction film; 240. Polyimide insulation layer; 250. Functionally graded alloy layer; 300. S-band conformal antenna; 310. Radiating patch. DETAILED DESCRIPTION

[0015] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several variations and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0016] Reference Figures 1 to 4 In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0017] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0018] This invention provides a gradient thermal compensation micro-nanosatellite solar wing and antenna integrated device, comprising a solar wing and antenna integrated mechanism and a compression and release mechanism 5 symmetrically positioned on the four sides of the micro-nanosatellite body. The solar wing and antenna integrated mechanism comprises an outer panel 2, an inner panel 1, and a hinge locking mechanism 3. The hinge locking mechanism 3 is positioned between the outer panel 2 and the inner panel 1, and between the inner panel 1 and the satellite body. When the hinge locking mechanism 3 is retracted, the compression and release mechanism 5 locks the inner and outer panels 1 and 2 to the satellite body, with the patch surface of the inner panel 1 facing outward. After the satellite solar wing enters orbit, the compression and release mechanism 5 is unlocked, and the inner and outer panels 1 and 2 unfold, forming a "cross" shape. The folding mechanism combines SMA drive and mechanical ratchet dual-stage locking, ensuring high pointing accuracy and low manufacturing cost after deployment. Through triple innovations in materials, structure, and functionality, this patent resolves the inherent contradictions inherent in the separate design of micro-nanosatellite energy and communication systems, achieving breakthroughs in dimensions such as size, cost, and reliability. It possesses clear engineering value and market competitiveness.

[0019] In one embodiment, the inner panel 1 and outer panel 2 respectively include an ultra-thin flexible photovoltaic layer 100, a thermal-electrical-mechanical coupling isolation module 200, and an S-band conformal antenna 300, arranged from top to bottom. The polyimide substrate in the ultra-thin flexible photovoltaic layer 100 and the aluminum silicon carbide honeycomb panel 210 of the thermal-electrical-mechanical coupling isolation module 200 are bonded together using an epoxy resin adhesive. The polyimide substrate of the photovoltaic layer and the gradient material layer of the thermal-electrical-mechanical coupling isolation module 200 are then laminated together using a vacuum hot pressing process under high temperature and high pressure to form a seamless interface.

[0020] In one embodiment, the ultra-thin flexible photovoltaic layer 100 includes: a solar cell sheet 110 and a solar wing substrate 120; the solar cell sheet 110 and the solar wing substrate 120 are bonded by a space environment resistant epoxy resin adhesive; The solar cell 110 is a rigid GaAs cell; The solar wing substrate 120 is a carbon fiber reinforced polyimide substrate; A copper microstrip line is laser-etched on the back of a polyimide film between the solar cell 110 and the solar wing substrate 120, and an MPPT control circuit is integrated.

[0021] In one embodiment, the solar wing substrate 120 includes a carbon fiber cross grid disposed on the upper and lower surfaces and an aluminum honeycomb disposed between the carbon fiber cross grids. A polyimide film is attached between the solar cell sheet 110 and the solar wing substrate 120 for insulation.

[0022] In one embodiment, the thermal-electrical-mechanical coupling isolation module 200 includes an aluminum silicon carbide honeycomb panel 210, a silicon dioxide aerogel layer 220, a graphene directional heat conducting film 230, a polyimide insulating layer 240, and a functionally graded alloy layer 250; The aluminum silicon carbide honeycomb panel 210 is used for efficient heat dissipation and for supporting the ultra-thin flexible photovoltaic layer 100; The silica aerogel layer 220 is used to block heat conduction and reduce the temperature gradient between layers; The graphene directional heat conducting film 230 is used to directionally conduct heat away from local hot spots; The polyimide insulating layer 240 is used for electrical isolation and to reduce electromagnetic coupling loss; The functionally gradient alloy layer 250 is used to match the thermal expansion of the upper and lower layers and suppress interface stress.

[0023] The functionally graded alloy layer 250 and the dielectric substrate of the S-band conformal antenna 300 are connected using PEEK screws and silicon nitride ceramic thermal pads. Screw holes are appropriately spaced along the edge of each layer. The PEEK screws penetrate the three-layer structure, and the silicon nitride ceramic thermal pads are embedded between the screws and the substrate, blocking the heat conduction path.

[0024] Each layer of the thermal-electrical-mechanical coupling isolation module 200 is pressed together with the photovoltaic layer and the gradient material layer of the isolation module under high temperature and high pressure conditions through a vacuum hot pressing process to form a seamless interface.

[0025] In one embodiment, the functionally gradient alloy layer 250 is composed of a Ti / SiC composite material, and the thermal expansion coefficient can be gradually changed.

[0026] In one embodiment, the S-band conformal antenna 300 includes a serpentine radiating patch 310, a dielectric substrate, and a metal feed post. The S-band conformal antenna 300 includes the radiating patch 310 and a ground plane, with the radiating patch 310 and the ground plane being electromagnetically coupled and fed via an H-shaped gap.

[0027] An ultra-thin copper layer is deposited on the back of the substrate using magnetron sputtering, and an H-shaped gap is formed using photolithography. Integrated laser etching allows for simultaneous fabrication of the photovoltaic circuit and antenna feeder, reducing multiple steps and mass production costs. A serpentine routing layout maintains electrical continuity through elastic deformation during folding. The integrated design of the antenna, photovoltaic layer, and isolation module reduces the collapsed thickness and improves space utilization. Aerogel and gradient materials synergistically suppress thermal stress, ensuring communication stability across temperature ranges.

[0028] In one embodiment, the hinge locking mechanism 3 adopts a biaxial folding hinge, integrating an SMA wire-driven pre-tightening mechanism and a mechanical ratchet locking mechanism.

[0029] Preferably, the radiation patch 310 of the S-band conformal antenna 300 is fed through H-shaped slot coupling, and the length of the radiation patch 310 of the S-band conformal antenna 300 is 0.48 times the operating wavelength (λ), satisfying the relationship: Where c is the speed of light, f is the center frequency of the antenna, and εr is the dielectric constant of the substrate; The transverse length and wavelength of the H-shaped gap satisfy: Ws=0.12λ The longitudinal length meets the following requirements: Ls=0.25λ Preferably, the S-band conformal antenna 300 is a wave number synthesis array antenna, comprising 5×4 radiating patch 310 units, with a spacing of 0.8λ between adjacent units; Each unit adjusts the phase difference Δφ through the phase shifter to meet the wave number synthesis condition: Where k = 2π / λ is the wave number, d = 0.8λ is the unit spacing, and θ is the beam pointing angle.

[0030] The solar wing of the present invention can be folded onto a satellite with a relatively simple structure for application in micro-nano satellites. In addition, the solar wing design is different from that of existing technologies to achieve overall lightness, small envelope, low ground impact, high reliability and high scalability.

[0031] In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "connect," "fixed," etc. should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediary; or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0032] The above is a further detailed description of the present invention in conjunction with specific embodiments, and the specific implementation of the present invention cannot be considered to be limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention.

Claims

1. A gradient thermal compensation micro-nano satellite solar wing and antenna integrated device, characterized in that: It includes a solar wing and antenna integration mechanism and a compression and release mechanism symmetrically arranged on the four sides of the micro-nano satellite body. The solar wing and antenna integration mechanism includes an outer panel, an inner panel and a hinge locking mechanism; the hinge locking mechanism is arranged between the outer panel and the inner panel, and between the inner panel and the satellite body. When the compression and release mechanism is in the retracted state, it locks the inner panel and the outer panel on the satellite body, and the patch surface of the inner panel faces outward; after the satellite solar wing enters orbit, the compression and release mechanism is unlocked, the inner panel and the outer panel are unfolded, and the satellite solar wing forms a "cross" shape.

2. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 1 is characterized in that: The inner panel and the outer panel respectively include an ultra-thin flexible photovoltaic layer, a thermal-electrical-mechanical coupling isolation module and an S-band conformal antenna arranged from top to bottom.

3. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 2 is characterized in that: The ultra-thin flexible photovoltaic layer includes: a solar cell sheet and a solar wing substrate; The solar cell is a gallium arsenide rigid cell; The solar wing substrate is a carbon fiber reinforced polyimide substrate; The copper microstrip line is laser-etched on the back of the polyimide film between the solar cell and the solar wing substrate, and the MPPT control circuit is integrated.

4. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 3 is characterized in that: The solar wing substrate includes carbon fiber cross grids arranged on the upper and lower surfaces and aluminum honeycombs arranged between the carbon fiber cross grids.

5. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 2 is characterized in that: The thermal-electrical-mechanical coupling isolation module includes an aluminum silicon carbide honeycomb panel, a silicon dioxide aerogel layer, a graphene directional heat-conducting film, a polyimide insulation layer, and a functionally gradient alloy layer; The aluminum silicon carbide honeycomb panel is used for efficient heat dissipation and for supporting the ultra-thin flexible photovoltaic layer; The silica aerogel layer is used to block heat conduction and reduce the temperature gradient between layers; The graphene directional heat-conducting film is used to directionally conduct heat from local hot spots; The polyimide insulation layer is used for electrical isolation and reduces electromagnetic coupling loss; The functionally gradient alloy layer is used to match the thermal expansion of the upper and lower layers and suppress interface stress.

6. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 5 is characterized in that: The functional gradient alloy layer is composed of a Ti / SiC composite material, and its thermal expansion coefficient can be gradually changed.

7. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 2, characterized in that: The S-band conformal antenna includes a serpentine routing radiation patch, a dielectric substrate, and a metal feeding post.

8. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 1 is characterized in that: The hinge locking mechanism adopts a biaxial folding hinge and integrates an SMA wire driven pre-tightening mechanism and a mechanical ratchet locking mechanism.

9. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 2, characterized in that: The radiating patch of the S-band conformal antenna is fed through H-shaped slot coupling. An ultra-thin copper layer is deposited on the back of the substrate using a magnetron sputtering process, and the H-shaped slot is formed by photolithography. The length of the radiating patch of the S-band conformal antenna is 0.48 times the operating wavelength (λ), satisfying the relationship: Where c is the speed of light, f is the center frequency of the antenna, and εr is the dielectric constant of the substrate; The transverse length and wavelength of the H-shaped gap satisfy: Ws=0.12λ The longitudinal length meets the following requirements: Ls=0.25λ.

10. The gradient thermal compensation type micro-nano satellite solar wing and antenna integrated device according to claim 2, characterized in that: The S-band conformal antenna is a wave number synthesis array antenna, comprising 5×4 radiating patch elements, with a spacing of 0.8λ between adjacent elements; Each unit adjusts the phase difference Δφ through the phase shifter to meet the wave number synthesis condition: Where k = 2π / λ is the wave number, d = 0.8λ is the unit spacing, and θ is the beam pointing angle.

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