A large-temperature-difference v-shaped heat insulation device applied to a cryogenic space optical load

Abstract

The application discloses a large-temperature-difference V-shaped heat insulation device applied to a cryogenic space optical load, which comprises n layers of V-shaped heat insulation screen plates and a supporting leg assembly; the V-shaped heat insulation screen plate is of a V-shaped structure, the V-shaped openings of the n layers of V-shaped heat insulation screen plates face the optical load, and the n layers of V-shaped heat insulation screen plates are located between the optical load and a satellite platform; according to the distance from the V-shaped heat insulation screen plate to the optical load, the n layers of V-shaped heat insulation screen plates are respectively recorded as the first group of heat insulation screen plates, the second group of heat insulation screen plates, the n-th group of heat insulation screen plates, and the V-shaped included angle between the two heat insulation screen plates of each group is sequentially increased in the order of 1 to n; and the supporting leg assembly is used for supporting the V-shaped heat insulation screen plates. The application can guarantee the cryogenic performance of the optical load, thereby guaranteeing the imaging quality of the optical load.

Description

TECHNICAL FIELD

[0001] The application relates to a heat insulation device, in particular to a large-temperature-difference V-shaped heat insulation device applied to a deep low-temperature space optical load, and belongs to the technical field of space optical remote sensors. BACKGROUND

[0002] Low-temperature optical loads (such as space astronomical telescopes) working at the sun-earth libration point orbit (Lagrangian point) need to shield the influence of solar radiation and the normal-temperature satellite platform on the low-temperature optical load through a heat insulation device, so as to ensure that the optical load works at low temperature, thereby ensuring the imaging quality of the optical load and meeting the detection sensitivity requirement. The traditional heat insulation mode is to perform heat insulation by coating a plurality of layers of materials and heat insulation materials. With the deep low-temperature requirement of the optical load, the traditional heat insulation mode cannot meet the heat insulation requirement, which brings extremely adverse effects to the optical load. Therefore, ensuring the low temperature of the optical structure is a difficulty in the development of the space optical load. SUMMARY

[0003] The application aims to overcome the above-mentioned defects, provide a large-temperature-difference V-shaped heat insulation device applied to a deep low-temperature space optical load, solve the technical problem that the existing heat insulation mode cannot meet the working requirement of the optical load, and ensure the low-temperature performance of the optical load, thereby ensuring the imaging quality of the optical load.

[0004] To achieve the above-mentioned application purposes, the application provides the following technical scheme.

[0005] A large-temperature-difference V-shaped heat insulation device applied to a deep low-temperature space optical load comprises n layers of V-shaped heat insulation panels and a support leg assembly.

[0006] The V-shaped heat insulation panel is of a V-shaped structure, 3<=n<=5, the V-shaped openings of the n layers of V-shaped heat insulation panels point to the optical load, and the n layers of V-shaped heat insulation panels are located between the optical load and the satellite platform.

[0007] According to the direction from near to far of the distance between the V-shaped heat insulation panel and the optical load, the n layers of V-shaped heat insulation panels are respectively recorded as the first layer of V-shaped heat insulation panel, the second layer of V-shaped heat insulation panel,..., and the n-th layer of V-shaped heat insulation panel, and the V-shaped included angles of the first layer of V-shaped heat insulation panel, the second layer of V-shaped heat insulation panel,..., and the n-th layer of V-shaped heat insulation panel increase in turn.

[0008] The support leg assembly is used for supporting the V-shaped heat insulation panel.

[0009] Further, the included angle range of the n layers of V-shaped heat insulation panels is 120-180 degrees.

[0010] Further, the plane passing through the vertex of the included angle of each layer of V-shaped heat shield plate is the symmetry plane of the V-shaped heat shield device, and the included angle between the parts of the adjacent two layers of V-shaped heat shield plates located on the same side is greater than or equal to 7°.

[0011] Further, when the sunlight is directly involved in radiation, the outer envelope size of the n-layer V-shaped heat shield plate is related to the optical load size and the sunlight irradiation direction.

[0012] The n-layer V-shaped heat shield plate completely blocks all possible irradiation directions of the sunlight; the outer envelope margin of the n-1 to 1 layer V-shaped heat shield plate gradually decreases, each layer of V-shaped heat shield plate is only visible to the adjacent layer of V-shaped heat shield plate, and the optical load is only visible to the first layer of V-shaped heat shield plate, and the sunlight is only visible to the n-layer V-shaped heat shield plate.

[0013] Further, the support leg assembly is used to support both sides of the V-shaped heat shield plate.

[0014] The support leg assembly comprises a first support leg and a second support leg.

[0015] The first end of the first support leg is fixedly connected to the n-th heat shield plate, and the second end of the first support leg is fixedly connected to the first heat shield plate after passing through the n-1 to 2 heat shield plates, and the n-1 to 2 heat shield plates are fixedly connected to the first support leg.

[0016] The first end of the second support leg is fixed to the satellite platform, the n to 2 heat shield plates are provided with through holes, the second end of the second support leg passes through the n to 2 heat shield plates through the through holes and is fixedly connected to the first heat shield plate, and there is no contact between the through holes of the n to 2 heat shield plates and the second support leg.

[0017] Further, the first support leg and the second support leg form a V-shaped structure opposite to the direction of the V-shaped heat shield plate.

[0018] The first support leg and the second support leg are fixedly connected to the V-shaped heat shield plate or the satellite platform through the support leg fixing seat.

[0019] Further, the V-shaped heat shield plate is a laminated plate structure bonded together, comprising a V-shaped heat shield plate outer panel, a V-shaped heat shield plate honeycomb and a V-shaped heat shield plate inner panel, and the V-shaped heat shield plate honeycomb is arranged between the V-shaped heat shield plate outer panel and the V-shaped heat shield plate inner panel.

[0020] Further, the V-shaped heat shield plate honeycomb comprises two groups of honeycomb plates in the shape of flat plates, and the two groups of honeycomb plates are reinforcedly connected at the vertex of the included angle of the V-shaped heat shield plate through a V-shaped heat shield reinforcing sheet, and the V-shaped heat shield reinforcing sheet is used to fix the V-shaped included angle of the V-shaped heat shield plate and increase the structural rigidity and strength.

[0021] The V-shaped heat shield reinforcing piece is a V-shaped angle piece processed from an aluminum plate or an aluminum block.

[0022] Further, the outer panel and the inner panel of the V-shaped heat shield panel are both multilayer coating structures with a reflectivity of greater than or equal to 98%;

[0023] In a direction close to the optical load as the inner direction and a direction away from the optical load as the outer direction, the multilayer coating structure comprises, from the inside to the outside, a high-purity aluminum base, an anodization treatment layer, a PVD silver layer, a silicon dioxide layer (20), and a titanium oxide layer.

[0024] The purity of the high-purity aluminum base is greater than or equal to 98%, and the purity of the PVD silver layer is greater than or equal to 99.99%.

[0025] Further, the first support leg and the second support leg are made of CFRP carbon fiber / cyanate composite material.

[0026] The first support leg and the second support leg are internally embedded with an invar inner bushing, which is used to connect the support leg fixing seat.

[0027] Compared with the prior art, the present application has at least one of the following beneficial effects:

[0028] (1) The present application creatively proposes a large-temperature-difference V-shaped heat shield device applied to a deep cryogenic space optical load, which can reflect the heat of a satellite platform to a cold space, guarantee the low-temperature performance of the optical load, and thus guarantee the imaging quality of the optical load.

[0029] (2) The present application uses a high-reflectivity radiation shielding panel to effectively isolate the radiation between the low-temperature optical load and the satellite platform, can provide a stable, deep cryogenic temperature environment for the space optical load, reduce the influence of the satellite platform radiation on the optical load, and thus provide protection for the imaging quality of the optical load.

[0030] (3) The present application gives the preferred range of the number of layers and the angle of the V-shaped heat shield panel, in which range, the heat flow from the satellite platform and the sun can be effectively shielded through the intralayer thermal resistance and the interlayer reflection, the heat can be continuously dissipated to the deep cold space through emission and reflection under the action of the reflecting surface and the opening angle in the transmission process, and the overall weight and volume of the device can be controlled within a certain range.

[0031] (4) The V-shaped heat shield panel of the present application emits (or reflects) the heat absorbed from various directions to the cold space through several reflections between the layers, which can realize autonomous heat dissipation.

[0032] (5) The present application adopts a three-layer sandwich honeycomb structure, which not only reduces the weight of the heat shield and improves the structural stiffness, but also guarantees the structural mechanical properties while meeting the heat insulation requirements.

[0033] (6) The present application adopts independent support leg assemblies, which ensure radiation and heat insulation, avoid direct contact between the traditional coated multilayer insulation assemblies and the optical load or satellite platform, and between adjacent layers of the self-insulation screen, reduce the contact heat leakage caused by the traditional coating method, and do not block the external radiation cooling of the low-temperature system through the surface of the self-insulation screen. BRIEF DESCRIPTION OF DRAWINGS

[0034] Figure 1 Figure (a) is a schematic diagram of the V-shaped insulation device of the present application, and (b) is a cross-sectional view along the symmetry plane of the vertex of the V-shaped angle of the insulation screen;

[0035] Figure 2 Figure is a schematic diagram of the tangential installation of the V-shaped insulation device of the present application;

[0036] Figure 3 Figure is a schematic diagram of the structure of the support leg assembly of the present application;

[0037] Figure 4 Figure is a schematic diagram of the satellite platform reflection and diffusion of the V-shaped insulation device of the present application;

[0038] Figure 5 Figure is a schematic diagram of the composition of the V-shaped insulation screen plate of the present application.

[0039] Figure 6 Figure is a schematic diagram of the panel film layer of the V-shaped insulation screen plate of the present application;

[0040] In the figure, 1 is a V-shaped insulation screen plate, 2 is a support leg assembly, 3 is a V-shaped insulation screen reinforcing sheet, 4 is a V-shaped insulation screen plate outer panel, 5 is a V-shaped insulation screen plate honeycomb, 6 is a V-shaped insulation screen plate inner panel, 7 is a first support leg, 8 is a second support leg, 9 is a first support leg fixing seat, 10 is a second support leg fixing seat, 11 is a third support leg fixing seat, 12 is a fourth support leg fixing seat, 13 is a fifth support leg fixing seat, 14 is an invar inner bushing, 15 is a titanium alloy gasket, 16 is a titanium alloy screw, 17 is an aluminum base, 18 is an anodized treatment layer, 19 is a PVD silver layer, 20 is a silicon dioxide layer, and 21 is a titanium oxide layer. DETAILED DESCRIPTION

[0041] The characteristics and advantages of the present application will become more apparent with the following detailed description of the present application.

[0042] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Unless specifically indicated otherwise, the drawings are not necessarily to scale.

[0043] The application provides a large-temperature-difference V-shaped heat insulation device applied to a deep cryogenic space optical load.

[0044] In a specific embodiment, the large-temperature-difference V-shaped heat insulation device applied to the deep cryogenic space optical load comprises a V-shaped heat shield plate 1 and a support leg assembly 2; the V-shaped heat shield plate 1 is internally embedded with a V-shaped heat shield reinforcing sheet 3, the V-shaped heat shield reinforcing sheet 3 is connected with the support leg assembly 2, and the support leg assembly 2 is connected with the V-shaped heat shield plate 1 to support the V-shaped heat shield plate 1.

[0045] In a specific embodiment, each layer of the V-shaped heat shield plate 1 forms different included angles, the included angles range from 120° to 180°, which is beneficial to heat radiation and heat dissipation, the angle of each layer increases from top to bottom, the unilateral included angle between layers is greater than 7°, which is beneficial to reducing the number of repeated reflection and reabsorption of heat between structures, beneficial to heat radiation and dissipation, improving the emission efficiency and quickly scattering heat from the opening angle to the cold space.

[0046] In a specific embodiment, the V-shaped heat shield plate 1 is in the form of a rigid V-shaped multilayer heat shield plate, the V-shaped heat shield plate 1 can be provided with 3 to 5 layers of structure, the integrated radiation heat insulation equivalent thermal resistance of more than three layers is greater than or equal to 6000 ℃ / W, and more than 5 layers will lead to a decrease in heat insulation and heat dissipation efficiency, that is, the increase in structure size and weight cannot bring a substantial performance improvement.

[0047] In a specific embodiment, the support leg assembly 2 is in the form of an inverted V shape, each V-shaped heat shield plate 1 is connected with the support leg fixed seat, and each group of support leg assemblies 2 is directly connected with a single heat shield plate and passes through other heat shield plates without contact through the reserved holes.

[0048] In a specific embodiment, the V-shaped heat shield plate 1 is formed by bonding a V-shaped heat shield plate outer panel 4, a V-shaped heat shield plate honeycomb 5 and a V-shaped heat shield plate inner panel 6, and forms a laminate structure, and the V-shaped heat shield reinforcing sheet 3 is an aluminum sheet (block) embedded in the honeycomb and used for connecting with the support leg fixed seat, and the heat shield reinforcing sheet 3 is designed according to the specific mechanical interface and structural strength.

[0049] In a specific embodiment, each group of support leg assemblies 2 comprises a first support leg 7, a second support leg 8, a first support leg fixed seat 9, a second support leg fixed seat 10, a third support leg fixed seat 11, a fourth support leg fixed seat 12, a fifth support leg fixed seat 13 and an invar inner bushing 14, each support leg fixed seat connects the V-shaped heat shield plate 1 with the support leg, plays a supporting role and unloads the stress caused by the material deformation caused by the large temperature difference. The titanium alloy gasket 15 and the titanium alloy screw 16 are used for fastening connection between each group of support legs and the fixed seat thereof, and are used for heat insulation connection of the support leg assembly.

[0050] In a specific embodiment, the outer panel 4 and the inner panel 6 of the V-shaped heat shield panel are made of a high-reflectivity material, which is composed of a 98% high-purity aluminum base 17 and a plurality of layers of films, from the inside to the outside, the plurality of layers of films are in turn: an anodization treatment layer 18, a PVD silver layer 19 with a purity of 99.99%, a silicon dioxide layer 20, and a titanium oxide layer 21, forming a 98% reflection to light. The material of the high-purity aluminum 17 panel is 1085 pure aluminum. In order to meet the thermal performance of the equivalent thermal resistance of the comprehensive radiation of more than three layers ≥6000℃ / W, the reflectivity of the high-purity aluminum 17 panel reaches 98% while ensuring a certain heat diffusion capacity and temperature uniformity of the panel.

[0051] In a specific embodiment, the material of the first support leg 7 and the second support leg 8 is CFRP carbon fiber composite material and cyanate ester polymer.

[0052] In a specific embodiment, when there is direct sunlight involved in radiation, the outer envelope size of the n-layer V-shaped heat shield panel 1 is related to the load size and the sunlight irradiation angle. It is required that the n-layer V-shaped heat shield panel 1 can completely block all possible irradiation directions of sunlight, so as to ensure that sunlight will not irradiate the optical load; the outer envelope margin of the n-1 to 1 layer V-shaped heat shield panel 1 gradually decreases, and it should be ensured that each layer of the V-shaped heat shield panel 1 is only visible to the adjacent layer of the panel, while the optical load is only visible to the first layer of the V-shaped heat shield panel 1, and the sunlight is only visible to the outermost layer of the V-shaped heat shield panel 1.

[0053] The application provides a large-temperature-difference V-shaped heat shield device applied to a deep cryogenic space optical load. The device solves the problem of radiation heat leakage in a low-temperature optical load while not affecting the radiation refrigeration of the main body of the optical load, and ensures the low-temperature performance of the optical load. The panel assembly and support structure of the V-shaped heat shield play a role in heat insulation, and reflect the heat of the satellite platform to the cold space (deep cold space of 3-4K space), so as to ensure the low-temperature performance of the optical load, thereby directly affecting the imaging quality of the optical load. The traditional heat insulation mode is to coat and insulate by heat insulation materials, but with the requirement of deep cryogenic optical load, the traditional heat insulation mode cannot meet the heat insulation requirement, and also limits the passive radiation refrigeration of the optical load, which brings extremely adverse effects to the optical load. Therefore, the low-temperature guarantee of the optical load structure is a key link in the development of space optical load. Figure 1The optical load at the upper end of the heat insulation device of the application can radiate refrigeration through the high-emissivity structure surface thereof, and part of the radiated heat is reflected by the device of the application to the space above; after the satellite platform radiation and the direct solar heat flow below the application reach the application, most of the heat is reflected by the heat shield of the device of the application, and a small part of the absorbed heat is dissipated to the surrounding space through the re-radiation and limited reflection of the surface of the heat shield during interlayer transmission, and only a very small part of the heat is transmitted to the optical load through heat conduction and radiation superposition, thereby reducing the heat load of the heat flow optical system refrigeration.

[0054] The application can provide a stable and deep low-temperature temperature environment for the space optical load by effectively isolating the radiation between the space low-temperature optical load and the satellite platform through the high-reflectivity radiation shielding plate, reduce the influence of the satellite platform radiation on the optical load, and thus provide protection for the imaging quality of the optical load.

[0055] The application has a certain autonomous heat dissipation capacity through the radiation shielding plate with an angle, can emit (or reflect) the heat absorbed by each layer from each side to the cold space through several times of reflection between layers.

[0056] The application adopts a three-layer sandwich honeycomb structure, so that the heat shield not only reduces the weight and improves the structural stiffness, but also meets the heat insulation while ensuring the required structural mechanical properties.

[0057] The V-shaped heat shield of the application adopts an independent support leg assembly, which ensures radiation insulation, avoids contact with the structure body, reduces the contact heat leakage caused by the traditional cladding method, and does not block the external radiation refrigeration of the low-temperature optical load system through the surface thereof.

[0058] Embodiment:

[0059] As shown in Figure 1 A large-temperature-difference V-shaped heat insulation device applied to a deep low-temperature space optical load is installed between the optical load and the satellite platform of a remote sensor, and is used for shielding the satellite platform and other satellite platforms, and comprises a V-shaped heat shield plate 1, a V-shaped heat shield support leg assembly 2 and a V-shaped heat shield reinforcing sheet 3.

[0060] The V-shaped heat shield plate 1 is V-shaped, and the support leg assembly 2 is lower V-shaped; the V-shaped heat shield support leg assembly 2 is installed with the satellite platform or the support platform; the V-shaped heat shield plate 1 is internally embedded with a V-shaped heat shield reinforcing sheet 3, and the V-shaped heat shield reinforcing sheet 3 is connected with the support leg assembly 2; the third layer of the V-shaped heat shield plate 1 is installed on the third support leg fixing seat 11 of the support leg assembly 2 through a screw; the second layer of the V-shaped heat shield plate 1 is connected with the second support leg fixing seat 10 of the support leg assembly 2; and the first layer of the V-shaped heat shield plate 1 is connected with the first support leg fixing seat 9 of the support leg assembly 2. Since the specific stiffness of the CFRP carbon fiber composite material is high and the thermal conductivity is low, the CFRP carbon fiber composite material is selected as the main support material of the support leg assembly 2, most of the heat in the direct heat transfer path is isolated, and part of the radiation heat is reflected to the cold space by the V-shaped screen.

[0061] As shown in Figure 2 , the V-shaped heat shield plate 1 adopts a honeycomb sandwich structure design, which is composed of a V-shaped heat shield plate outer panel 4, a V-shaped heat shield plate honeycomb 5, and a V-shaped heat shield plate inner panel 6, and forms a laminated plate structure, which not only enhances the overall stiffness but also reduces the weight, and the relatively strong stiffness of the V-shaped heat shield plate 1 ensures the overall flatness of the screen plate and effectively reflects the satellite platform.

[0062] As shown in Figure 3 , each group of support leg assemblies 2 includes a first support leg 7, a second support leg 8, a first support leg fixing seat 9, a second support leg fixing seat 10, a third support leg fixing seat 11, a fourth support leg fixing seat 12, a fifth support leg fixing seat 13, and an invar inner bushing 14. The invar inner bushing 14 is first used as an internal support to effectively reduce the local stress on the first support leg 7 and the second support leg 8 caused by large temperature differences due to its low expansion coefficient, and then each support leg fixing seat is installed to the required position.

[0063] As shown in Figure 4 , different included angles are formed between adjacent V-shaped heat shield plates, and the included angle ranges from 120° to 180°, which is beneficial to heat radiation and heat dissipation, and the angle increases from top to bottom to ensure that the single-sided angle between layers meets the design requirements. Figure 4 , the optical load is arranged above the V-shaped heat shield plate 1, the satellite platform is arranged below the V-shaped heat shield plate 1, and the V-shaped heat shield plate 1, the optical load, and the satellite platform are in the deep cold space in space.

[0064] As shown in Figure 5 , the V-shaped heat shield plate 1 is composed of a V-shaped heat shield plate outer panel 4, a V-shaped heat shield plate honeycomb 5, and a V-shaped heat shield plate inner panel 6, and forms a laminated plate structure.

[0065] As shown in Figure 6As shown, in order to ensure that the mirror surface reaches 98% high reflectivity, the V-shaped heat shield plate outer panel 4 and the V-shaped heat shield plate inner panel 6 are high-reflectivity materials, and 98% high-purity aluminum base 17 forms an anodized layer 18 after surface anodizing treatment, and then a plurality of layers of films are plated from inside to outside in sequence: a PVD silver layer 19 with a purity of 99.99%, a silicon dioxide layer 20, and a titanium oxide layer 21.

[0066] The V-shaped heat shield and the supporting leg structure of the present application realize shielding of the satellite platform. The heat shield adopts a multi-layer sandwich structure, the honeycomb layer of which reduces weight, improves structural rigidity, improves thermal resistance, and reduces interlayer heat leakage; and the high reflectivity of the panel reflects infrared energy, and through different angles between the screens, the heat is reflected away, thereby playing a heat dissipation role.

[0067] The present application has been described in detail with reference to specific embodiments and exemplary examples, but these descriptions are not to be construed as limiting the present application. Those skilled in the art understand that various equivalent substitutions, modifications or improvements can be made to the technical solutions and embodiments of the present application without departing from the spirit and scope of the present application, and these all fall within the scope of the present application. The protection scope of the present application is subject to the appended claims.

[0068] The contents not described in detail in the specification of the present application are known to those skilled in the art.

Claims

1. A large temperature difference V-shaped thermal insulation device applied to a cryogenic space optical load, characterized in that, It includes n layers of V-shaped heat insulation panels (1) and support leg assemblies (2); The V-shaped heat shield (1) has a V-shaped structure, 3≤n≤5, and the V-shaped opening of the n-layer V-shaped heat shield (1) points towards the optical load. The n-layer V-shaped heat shield (1) is located between the optical load and the satellite platform. According to the direction from near to far between the V-shaped heat insulation panel (1) and the optical load, the n layers of V-shaped heat insulation panels (1) are respectively denoted as the first layer of V-shaped heat insulation panel, the second layer of V-shaped heat insulation panel, ... the nth layer of V-shaped heat insulation panel. The included angle of the V-shape of the first layer of V-shaped heat insulation panel, the second layer of V-shaped heat insulation panel, ... the nth layer of V-shaped heat insulation panel increases sequentially. The support leg assembly (2) is used to support the V-shaped heat insulation panel (1).

2. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical payload according to claim 1, characterized in that, The included angle of the n-layer V-shaped heat insulation panel (1) ranges from 120° to 180°.

3. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical load according to claim 1, characterized in that, The plane passing through the apex of the included angle of each layer of V-shaped heat insulation panel (1) is the symmetry plane of the V-shaped heat insulation device. With the symmetry plane as the boundary, the included angle between the parts of two adjacent layers of V-shaped heat insulation panels (1) located on the same side is ≥7°.

4. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical load according to claim 1, characterized in that, When direct sunlight participates in radiation, the outer envelope size of the n-layer V-shaped heat insulation panel (1) is related to the optical load size and the direction of sunlight irradiation; The nth layer of V-shaped heat insulation panel completely blocks all possible directions of sunlight; the outer envelope of the n-1 to 1st layer of V-shaped heat insulation panel gradually shrinks, each layer of V-shaped heat insulation panel (1) is only visible to the adjacent layer of V-shaped heat insulation panel (1), and the optical load is only visible to the 1st layer of V-shaped heat insulation panel, and sunlight is only visible to the nth layer of V-shaped heat insulation panel.

5. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical payload according to claim 1, characterized in that, The support leg assembly (2) is used to support both sides of the V-shaped heat insulation panel (1); The support leg assembly (2) includes a first support leg (7) and a second support leg (8); The first end of the first support leg (7) is fixedly connected to the nth heat insulation plate, the second end of the first support leg (7) passes through the n-1 to the 2nd heat insulation plates and is fixedly connected to the 1st heat insulation plate, and the n-1 to the 2nd heat insulation plates are fixedly connected to the first support leg (7). The first end of the second support leg (8) is fixed to the satellite platform. The nth to 2nd heat insulation panels are provided with through holes. The second end of the second support leg (8) passes through the nth to 2nd heat insulation panels through the through holes and is fixedly connected to the first heat insulation panel. There is no contact between the through holes of the nth to 2nd heat insulation panels and the second support leg (8).

6. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical payload according to claim 5, characterized in that, The first supporting leg (7) and the second supporting leg (8) form a V-shaped structure opposite to the direction of the V-shaped heat insulation panel (1); The first support leg (7) and the second support leg (8) are fixedly connected to the V-shaped heat insulation panel (1) or the satellite platform through the support leg fixing seat.

7. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical load according to claim 1, characterized in that, The V-shaped heat insulation panel (1) is a laminated structure bonded together, including an outer panel (4), a honeycomb (5), and an inner panel (6). The honeycomb (5) is located between the outer panel (4) and the inner panel (6).

8. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical payload according to claim 7, characterized in that, The V-shaped heat shield panel honeycomb (5) comprises two groups of flat plate-shaped honeycomb panels, which are reinforcedly connected at the vertex of the V-shaped heat shield panel (1) by a V-shaped heat shield panel reinforcing sheet (3) for fixing the V-shaped angle of the V-shaped heat shield panel (1) and increasing the structural rigidity and strength. The V-shaped heat shield panel reinforcing sheet (3) is a V-shaped angle sheet processed from an aluminum plate or an aluminum block.

9. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical payload according to claim 7, characterized in that, The V-shaped heat shield panel outer panel (4) and the V-shaped heat shield panel inner panel (6) are both multilayer coating structures with a reflectivity of ≥98%. In the direction close to the optical load as the inside and the direction away from the optical load as the outside, the multilayer coating structure comprises, from the inside to the outside, a high-purity aluminum base (17), an anodization treatment layer (18), a PVD silver layer (19), a silicon dioxide layer (20) and a titanium oxide (21) layer. The purity of the high-purity aluminum base (17) is ≥98%, and the purity of the PVD silver layer (19) is ≥99.99%.

10. The large temperature difference V-type thermal insulation device applied to a cryogenic space optical payload according to claim 5, wherein, The materials used for the first support leg (7) and the second support leg (8) are CFRP carbon fiber / cyanate ester composite materials. The first support leg (7) and the second support leg (8) are internally embedded with an invar inner bushing (14) for connecting the support leg fixing seat.

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