CN219806970U - Satellite platform configuration for detecting earth-centered high-orbit space gravitational wave - Google Patents

Abstract

The utility model discloses a satellite platform configuration for detecting earth-centered high-orbit space gravitational wave, which comprises the following components: the star and set up the sunshading board at star top, the sunshading board includes the base plate, install the sun sensor at base plate top border position, install at the body dress formula solar array at base plate top and be used for the support column of being connected with the star, the star includes the shell of the inside central point of octagon right angle polyhedron structure of shell, set up the central force-bearing section of thick bamboo and set up a plurality of shear force walls between central force-bearing section of thick bamboo and shell, divide into core load cabin, peripheral load cabin, platform equipment cabin and propulsion equipment cabin with the star through central force-bearing section of thick bamboo and shear force wall. According to the solar cell array sensor, the sun shield is arranged, the solar cell array can be used for carrying out shading and heat insulation on a star, and meanwhile, the requirements of space gravitational wave detection on the stability, thermal control, mass center, self-gravitational balancing and the like of a satellite structure are met by adopting the cabin type configuration design of the shell, the shear wall and the central bearing cylinder.

Description

Satellite platform configuration for detecting earth-centered high-orbit space gravitational wave

Technical Field

The utility model relates to the technical field of satellite platform configuration, in particular to a satellite platform configuration for detecting earth-centered high-orbit space gravitational waves.

Background

Compared with ground detection, the space gravitational wave detection targets are concentrated in the low frequency range of 0.1 mHz-1 Hz, so that gravitational wave sources which are rich in types, huge in quantity and widely distributed on various distances in the cosmic space can be detected. Current space gravitational wave detection schemes can be largely divided into earth orbit schemes represented by "Tianqin scheme" and orbit around the sun schemes represented by LISA, wherein one major challenge faced by earth orbit schemes is the effect of solar azimuth changes on satellite thermal control.

The thermal control, structural stability, mass center and self-attraction of the key parts of the space gravitational wave detection spacecraft have extremely high requirements, for example, the temperature stability of an optical platform is required to reach mu K/Hz ^1/2 Magnitude, self-attraction induced acceleration offset is less than 1nm/s ² This presents a significant challenge to both overall design and platform development. The utility model provides a satellite platform configuration for detecting earth center high-orbit space gravitation waves, which has the advantages that high requirements are put on the configuration of a spacecraft, the temperature control requirements for ensuring the load under the action of solar irradiation and an internal heat source are considered, the structural stability during launching and in-orbit are also met, and the symmetry of the in-satellite layout is considered to facilitate quality and self-gravitation balancing.

Disclosure of Invention

The embodiment of the utility model provides a satellite platform configuration for detecting earth-centered high-orbit space gravitational waves, which can provide an ultra-static and ultra-stable working environment for core load, thereby meeting the requirements of space gravitational wave detection on the stability, thermal control, mass center, self-gravitational balancing and the like of a satellite structure.

In view of this, the present utility model provides a satellite platform configuration for geocentric high orbit space gravitational wave detection, comprising: the sun shield is arranged at the top of the star;

the sun shield comprises a base plate, a sun sensor arranged at the edge position of the top of the base plate, a body-mounted solar cell array arranged at the top of the base plate and a support column connected with the star;

the star comprises a shell with an octagonal right-angle polyhedron structure, a central bearing cylinder arranged at the central position inside the shell, and a plurality of shear walls arranged between the central bearing cylinder and the shell;

the shell divides the star body into a core load cabin, a peripheral load cabin, a platform equipment cabin and a propulsion equipment cabin through the central bearing cylinder and the shear wall.

Optionally, a core load shielding cover and a movable optical machine component are arranged in the core load cabin;

the core load shielding cover is positioned in the central bearing cylinder;

the movable optical machine component is installed in the central bearing cylinder by adopting an integrated structure and is partially nested with the core load shielding cover.

Optionally, an inertial front-end circuit, a charge management unit, a laser amplifier unit, a scientific load distribution unit, a locking release control unit, a comprehensive electronic unit and a radiometer are arranged in the peripheral load cabin;

wherein the integrated electronic unit and the laser amplifier unit are both mounted on the inner side wall of the housing;

the radiometer is arranged on the outer side wall of the central bearing cylinder;

the inertia front-end circuit, the charge management unit, the laser unit, the scientific load distribution unit and the locking release control unit are all arranged on the shear wall.

Optionally, an inter-satellite link antenna, a GNSS receiver, a power supply control and distribution unit and a transponder are arranged in the platform equipment cabin;

wherein, the inter-satellite link antenna and the GNSS receiver are both arranged on the inner side wall of the shell;

the power control and distribution unit and the transponder are both mounted on the shear wall.

Optionally, a track-controlled propulsion control unit, a high-pressure gas cylinder, a star-sensitive circuit list, a star-based computer, an optical fiber gyroscope and a storage battery pack are arranged in the propulsion equipment cabin;

wherein the fiber optic gyroscope is mounted on the inner side wall of the housing;

the rail-controlled propulsion control unit, the star-sensitive circuit unit, the satellite-borne computer and the storage battery pack are all arranged on the shear wall;

the high-pressure gas cylinder is arranged at the inner bottom of the shell.

Optionally, the star body is further provided with an overhanging part;

the overhanging component comprises a star sensor, a docking ring, a data transmission antenna, a micro propeller and a rail-controlled propeller, wherein the star sensor is arranged on the shell, the docking ring and the data transmission antenna are arranged at the bottom of the shell, and the micro propeller and the rail-controlled propeller are symmetrically arranged on the outer side wall of the shell.

Optionally, the substrate and the bottom of the housing are both provided with inter-satellite connection interfaces for serial connection of an arrow and a three-satellite.

Optionally, the shell, the shear wall and the substrate are all made of carbon fiber composite material skin honeycomb structure plates.

Optionally, two ends of the support column are respectively connected with the substrate and the star bolt;

the support column is made of titanium alloy or aluminum alloy.

Optionally, a heat dissipation surface is disposed on the housing.

From the above technical solutions, the embodiment of the present utility model has the following advantages: according to the satellite platform structure, the sun shield is arranged at the top of the star, a body-mounted non-unfolding solar cell array is adopted on one side of the sun shield, so that the interference generated by the movement of a solar cell panel unfolding mechanism is avoided, meanwhile, under the observation mode of 3+3 months, the telescope and the star side plate are prevented from being directly irradiated by the sun, the temperature stability of a core area is conveniently controlled, and the solar heat flow and the electronic waste heat can be attenuated one by adopting the cabin type structural design of the shell, the shear wall and the central bearing barrel, and the requirements of space gravitational wave detection on the structural stability, the thermal control, the mass center, the self-gravitation balancing and the like of the satellite are further met.

Drawings

FIG. 1 is a schematic view of a satellite platform configuration for geocentric high orbit space gravitational wave detection in accordance with an embodiment of the present utility model;

FIG. 2 is a schematic view of the structure of the star hidden +Z outer plate in the embodiment of the utility model;

FIG. 3 is a schematic diagram of the layout of an in-star device in an embodiment of the present utility model;

FIG. 4 is a schematic diagram of a prior art track three star formation;

wherein, the reference numerals are as follows:

100. a central force bearing cylinder 110, a core load shielding case 111, a movable optical machine component 120, a radiometer 210, +X+Y_1 shear wall 211, a power supply control and distribution unit 220, +X+Y_2 shear wall 221, a satellite-borne computer 230, +Y shear wall 231, a satellite-borne circuit unit 232, a rail propulsion control unit 233, a lock release control unit 234, a scientific load distribution unit 240, -X-Y shear wall 241, a laser unit 242, a charge management unit 243, an inertial front end circuit 250, -X+Y shear wall 260, -Y shear wall 270, +X-Y_2 shear wall 271, a battery pack 280, +X-Y_1 shear wall, 281, transponder, 300, +z outer plate, 301, star sensor, 310, -Z outer plate, 311, docking collar, 312, data transmission antenna, 313, high pressure gas cylinder, 320, +x outer plate, 321, GNSS receiver, 322, inter-satellite link antenna, 330, +x+y outer plate, 331, micro-propeller, 332, fiber optic gyro, 340, +y outer plate, 341, rail-controlled propeller, 350, -x+y outer plate, 351, laser amplifier unit, 360, -X outer plate, 361, integrated electronics unit, 370, -X-Y outer plate, 380, -Y outer plate, 390, +x-Y outer plate, 400, substrate, 401, sun sensor, 402, body mounted solar cell array, 403, support column.

Detailed Description

In order to make the present utility model better understood by those skilled in the art, the following description will clearly and completely describe the technical solutions in the embodiments of the present utility model with reference to the accompanying drawings, and it is apparent that the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

In the description of the present utility model, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

The inventors found that: for the gravitational wave detection task of the earth center high orbit, a three-star formation mode (as shown in fig. 4) can be selected, gravitational wave signals are measured through inter-satellite laser interferometry, each satellite is required to be provided with two movable optical-mechanical assemblies, and the inter-satellite laser links are required to be kept unobstructed and can not be blocked by structural components. In addition, the sun shield needs to shield the sun rays in a scientific observation period, so that the stars or the telescope are prevented from being directly irradiated by the sun, and the sun shield needs to be thermally decoupled with the stars through the supporting structure so as to reduce the solar heat flow transmitted to the stars as much as possible. In order to avoid interference of vibration generated by the moving parts on gravitational wave signals, the solar panel is in a body-mounted non-expanded structure, and because of the requirements of ultra-static and ultra-stable, the momentum wheel, liquid and other parts which can generate vibration or shake are not allowed to be used in the star.

Based on the structural configuration requirement of the gravitational wave detection satellite platform, the traditional satellite configuration has higher inheritance, and a satellite platform meeting the requirement is not available at present, so that a new satellite platform configuration is designed aiming at a ground center high-orbit gravitational wave detection task to meet the detection task requirement, and the structural design not only considers the thermal control requirement, but also needs to combine the requirements of the space gravitational wave detection task on the structural stability, the mass center and the self-gravitational balancing of the satellite platform. In addition, unlike other space tasks, the gravitational wave detection satellite of the earth's center high orbit needs to perform posture overturning before entering the ' 3+3 ' observation period, and the design of the sun shield in the thermal control design can ensure the shading required by posture overturning in advance.

The present utility model provides an embodiment of a satellite platform configuration for geocentric high orbit space gravitational wave detection, and particularly referring to fig. 1-3.

The satellite platform configuration for geocentric high orbit space gravitational wave detection in this embodiment includes: the star and set up the sunshading board at star top, the sunshading board includes base plate 400, install the sun sensor 401 at base plate 400 top border position, install body dress formula solar array 402 at base plate 400 top and be used for with star connection's support column 403, the star includes the shell of octagon right angle polyhedron structure, set up the central force-bearing cylinder 100 of the inside central position of shell and set up a plurality of shear walls between central force-bearing cylinder 100 and shell, shear wall connects shell and central force-bearing cylinder 100, the shell passes through central force-bearing cylinder 100 and shear wall and divides the star into core load cabin, peripheral load cabin, platform equipment cabin and propulsion equipment cabin.

It should be noted that: the satellite platform structure is characterized in that the sun shield is arranged at the top of the star, a solar cell array which is not unfolded is arranged on one side of the sun shield, the interference generated by the movement of a solar cell panel unfolding mechanism is avoided, meanwhile, under the observation mode of 3+3 months, the telescope and the star side plates are prevented from being directly irradiated by the sun, the temperature stability of a core area is convenient to control, and the cabin type structure design of the shell, the shear wall and the central bearing barrel 100 is adopted, so that the heat flow fluctuation and the frequency domain temperature noise which are transmitted into the core load shielding cover 110 can be reduced layer by layer through the heat capacity of a structural material, the thermal resistance of a structural interface, the cabin thermal decoupling mode, the solar heat flow and the electronic waste heat are attenuated layer by layer, and the requirements of space gravitational wave detection on the stability, the thermal control, the mass center, the self-gravitational balancing and the like of the satellite structure are further met.

The foregoing is an embodiment one of a satellite platform configuration for detecting a gravitational wave in a space of a geocentric high orbit, and the following is an embodiment two of a satellite platform configuration for detecting a gravitational wave in a space of a geocentric high orbit, referring to fig. 1 to 3.

The satellite platform configuration for geocentric high orbit space gravitational wave detection in this embodiment includes: the sun shield comprises a substrate 400, a sun sensor 401 arranged at the edge position of the top of the substrate 400, a body-mounted solar cell array 402 arranged at the top of the substrate 400 and a support column 403 used for connecting with the star, wherein the sun shield shields the star and is the only sunlight irradiation surface of the whole star, a cone of more than 90 degrees is provided, the corresponding shielding time is longer than 3 months, and the single-sided carrier-mounted solar cell array 402 supplies power for the star; the star comprises a shell with an octagonal right-angle polyhedron structure, a central bearing cylinder 100 arranged at the central position inside the shell and a plurality of shear walls arranged between the central bearing cylinder 100 and the shell, wherein the shell divides the star into a core load cabin, a peripheral load cabin, a platform equipment cabin and a propulsion equipment cabin through the central bearing cylinder 100 and the shear walls. It can be understood that the shell adopts an octagonal right-angle polyhedron structure, and comprehensively considers the requirements of structural stability, equipment layout, thermal control scheme, one-arrow-multiple-star emission and extra-star layout.

It should be noted that: firstly, in order to reduce the influence caused by solar angle change, the satellite adopts an alternate operation mode of '3 months measurement and 3 months standby', and the sun shield not only realizes the requirement of loading the solar cell array and the solar sensor 401, but also meets the size requirement of avoiding the direct solar star in the three month observation period. Specifically, the height of the star can be 600mm, the diameter of the star cross section outer envelope circle can be 3000mm, the diameter of the solar panel cross section outer envelope circle can be 4800mm, the size design can meet the requirement that sunlight cannot directly irradiate the side of the star when the sun incidence angle is the minimum of 45 degrees in the three-month observation period, and the size of the sun shield leaves a margin to meet the sun shield requirement of the attitude overturning in advance.

Some embodiments of the present utility model are described in detail below with reference to the accompanying drawings.

First, as shown in fig. 1, the body coordinate system (0-XYZ) of the satellite is defined as follows:

origin of coordinates 0: checking a mass connecting line center;

and Z axis: pointing to the sun shield along the origin of coordinates;

x axis: the angular bisector of the telescope lens barrel points to the three-star formation center;

y axis: right handed with the X, Z shaft.

As shown in FIG. 2, the outer shell consists of +X outer plate 320, +X+Y outer plate 330, +Y outer plate 340, -X+Y outer plate 350, -X outer plate 360, -X-Y outer plate 370, -Y outer plate 380, +X-Y outer plate 390, +Z outer plate 300 and-Z outer plate 310, wherein +X outer plate 320, +X+Y outer plate 330, +Y outer plate 340, -X+Y outer plate 350, -X outer plate 360, -X-Y outer plate 370, -Y outer plate 380 and +X-Y outer plate 390 are all side plates of a star, +Z outer plate 300 is the top plate of a star, -Z outer plate 310 is the bottom plate of a star; the number of shear walls is eight, including +X+Y_1 shear wall 210, +X+Y_2 shear wall 220, +Y shear wall 230, -X-Y shear wall 240, -X+Y shear wall 250, -Y shear wall 260, +X-Y_2 shear wall 270, +X-Y_1 shear wall 280.

Preferably, the +X outer plate 320, +X+Y outer plate 330, +Y outer plate 340, -X+Y outer plate 350, -X outer plate 360, -X-Y outer plate 370, -Y outer plate 380, +X-Y outer plate 390, +X+Y_1 shear wall 210, +X+Y_2 shear wall 220, +Y shear wall 230, -X-Y shear wall 240, -X+Y shear wall 250, -Y shear wall 260, +X-Y_2 shear wall 270 and +X-Y_1 shear wall 280 are rectangular; the sun visor, +Z outer plate 300 and-Z outer plate 310 are all regular hexagons; the central bearing cartridge 100 is cylindrical.

Specifically, the central bearing cylinder 100, the shear wall, the star side plates, the bottom plate and other star-shaped structural plates are mainly structurally connected by a simpler connection mode such as connection angle bars, embedded parts and the like.

As shown in fig. 2 and 3, a core load shield 110 and a movable optical-mechanical assembly 111 are disposed in the core load cabin, the core load shield 110 is located in the central bearing cylinder 100, and the movable optical-mechanical assembly 111 is installed in the central bearing cylinder 100 by adopting an integrated structure and is partially nested with the core load shield 110.

It will be appreciated that the central pod 100 is subjected to the primary loads of a spacecraft and may be made of a high modulus carbon fiber composite or an epoxy composite sized to phi 1200mm for attachment to a phi 1194 interface standard launch vehicle. The central bearing cylinder 100 and the telescope are located in the region to form a core load cabin, the movable optical machine component 111 is loaded, the laser interferometer and the inertial sensor are the core key of the detection task, and the central bearing cylinder 100 and the core load shielding cover 110 in the central bearing cylinder 100 can thermally decouple the core load from the internal environment of the star, so that a more stable working environment temperature is provided for the central bearing cylinder 100 and the telescope.

As shown in fig. 2 and 3, the area surrounded by the +y shear wall 230, -the x+y outer plate 350, -the X outer plate 360, -the X-Y outer plate 370, -the Y shear wall 260 and the central force bearing barrel 100 forms a peripheral load cabin, and two inertial front-end circuits 243, two charge management units 242, two laser units 241, two laser amplifier units 351, two scientific load distribution units 234, two locking release control units 233, one integrated electronic unit 361 and one radiometer 120 are arranged in the peripheral load cabin, wherein the integrated electronic unit 361 and the two laser amplifier units 351 are all arranged on the inner side wall of the housing; radiometer 120 is mounted on the outer sidewall of central force bearing cartridge 100; two inertial front-end circuits 243, two charge management units 242, two laser units 241, two scientific load distribution units 234, and two lock release control units 233 are mounted to the shear wall. Specifically, two inertial front-end circuits 243, two charge management units 242, two laser units 241 are symmetrically mounted on the-x+y shear wall 250 and the-X-Y shear wall 240, two laser amplifier units 351 are symmetrically mounted on the-x+y outer plate 350 and the-X-Y outer plate 370, two scientific load distribution units 234, two lock release control units 233 are symmetrically mounted on the +y shear wall 230 and the-Y shear wall 260, respectively, and an integrated electronic unit 361 is mounted inside the-X outer plate 360.

As shown in fig. 2 and 3, the area surrounded by the +x+y_1 shear wall 210, +x outer plate 320, +x-y_1 shear wall 280 and the central bearing cylinder 100 forms a platform equipment cabin, and an inter-satellite link antenna 322, two GNSS receivers 321, a power control and distribution unit 211 and a transponder 281 are arranged in the platform equipment cabin, wherein the inter-satellite link antenna 322 and the two GNSS receivers 321 are mounted on the inner side wall of the housing; the power control and distribution unit 211 and the transponder 281 are mounted on the shear wall. Specifically, the inter-satellite link antenna 322 is installed at the center of the inner side of the +x outer plate 320; two GNSS receivers 321 are symmetrically installed inside the +x outer plate 320 with the inter-satellite link antenna 322 as a center; the power control and distribution unit 211 and the transponder 281 are symmetrically disposed on the +x+y_1 shear wall 210 and the +x-y_1 shear wall 280.

As shown in fig. 2 and 3, two symmetrical cabins are formed between the +x+y_2 shear wall 220 and the +y shear wall 230 and between the-Y shear wall 260 and the +x-y_2 shear wall 270 and the area surrounded by the shell and the central bearing cylinder 100, the two cabins jointly form a propulsion equipment cabin, two rail-controlled propulsion control units 232, two high-pressure gas cylinders 313, two star-sensitive circuit units 231, a satellite-borne computer 221, two fiber-optic gyroscopes 332 and a storage battery 271 are arranged in the propulsion equipment cabin, wherein the two fiber-optic gyroscopes 332 are all arranged on the inner side wall of the shell; the two track-controlled propulsion control units 232, the two star-sensitive circuit units 231, the spaceborne computer 221 and the storage battery 271 are all arranged on the shear wall; two high pressure cylinders 313 are mounted at the bottom of the housing. Specifically, the two track-controlled propulsion control units 232 and the two star-sensitive circuit units 231 are symmetrically installed on the +y shear wall 230 and the-Y shear wall 260, the two fiber gyros 332 are symmetrically installed on the +x+y outer plate 330 and the +x-Y outer plate 390, and the spaceborne computer 221 and the storage battery 271 are symmetrically installed on the +x+y_2 shear wall 220 and the +x-y_2 shear wall 270.

It can be appreciated that since the gravitational effect of the spacecraft itself increases the acceleration noise of the proof mass in the measurement frequency band, fine design is performed centering on the proof mass, and mass distribution around the proof mass is uniform. The satellite platform configuration can facilitate balancing of mass centers and self-gravitation by adopting a symmetrical satellite structure and equipment layout so as to ensure the self-gravitation requirement of the inspection quality. Specifically, the distribution of the devices in the star is highly symmetrical along the X-axis, and the number of +x-direction devices on both sides of the Y-axis is small relative to the number of +x-direction devices, but the mass of the movable optical machine component 111 is large, so that the mass center and self-attraction balancing are facilitated by the layout.

It should be noted that: because the gravitational wave signal is extremely weak, the satellite should avoid using active heaters and heat pipes to dissipate heat in order to avoid additional disturbances interfering with the core load detection. According to the utility model, a high-power-consumption load single machine (the integrated electronic unit 361, the two laser amplifier units 351, the inter-satellite link antenna 322, the two GNSS receivers 321 and the two optical fiber gyroscopes 332) is arranged on the inner side wall of the shell, and other devices are arranged on the shear wall, so that passive heat exchange can be realized by means of pure radiation and solid heat conduction, and the effective load measurement of the space gravitational wave detection satellite is not influenced.

As shown in fig. 1, 2 and 3, the outside of the satellite body is further provided with an overhanging component, and the overhanging component comprises a star sensor 301 installed on the housing, a docking ring 311 and a data transmission antenna 312 installed at the bottom of the housing, and four micro-propellers 331 and two track-controlled propellers 341 symmetrically installed on the outer side wall of the housing. Specifically, four micro-propellers 331 are symmetrically distributed outside the +X+Y outer plate 330, -X+Y outer plate 350, -X-Y outer plate 370 and +X-Y outer plate 390; the two rail-controlled propellers 341 are symmetrically arranged outside the +Y outer plate 340 and the-Y outer plate 380; the sun sensor 401 and the star sensor 301 are respectively installed at the outside of the substrate 400 and the inside of the +z outer plate 300; the docking ring 311 and the data transmission antenna 312 are both mounted outside the-Z outer plate 310, wherein the data transmission antenna 312 is of an expandable structure.

It should be noted that: as shown in fig. 3, the length of the +y outer plate 340 and the-Y outer plate 380 is the shortest so that the thrust of the two orbital propellers 341 mounted outside the +y outer plate 340 and the-Y outer plate 380 is larger to meet the attitude control requirement required for the earth-centered high-rail gravitational wave detection task.

The substrate 400 and the bottom of the housing are provided with inter-satellite connection interfaces for serial connection of one arrow and three satellites, and in particular, the number of the inter-satellite connection interfaces may be plural, and the inter-satellite connection interfaces are located on the outer surface of the substrate 400 and the lower surface of the-Z outer plate 310.

The shell, the shear wall and the base plate 400 can be made of carbon fiber composite material skin honeycomb structural plates, the density is low, the modulus is high, the strength is high, the linear expansion coefficient is low, the influence of thermal deformation on the inspection quality and the inter-satellite optical path can be reduced, meanwhile, the carbon fiber composite material has extremely high thermal elasticity stability, and the thermal expansion coefficient can be further reduced by adopting reasonable layering, winding process or integrated structural design and other methods, so that the requirement of space gravitational wave detection task on structural stability can be met.

Specifically, two ends of the support column 403 are respectively connected with the substrate 400 and the +z outer plate 300 of the star by bolts, and the support column 403 may be made of titanium alloy or aluminum alloy.

It should be noted that: to ensure temperature stability of satellite core loads, the sun visor is isolated from the satellite body by support posts 403, and the transfer of solar heat and turbulence can be reduced by using high thermal resistance material outside the +z outer plate 300. The star inner center bearing barrel 100, the core load shielding cover 110 and the telescope lens barrel realize thermal decoupling of core load and an in-star thermal environment, and the interface design of the high thermal resistance of the in-star structure further isolates the influence of solar heat leakage and electronic waste heat on the temperature stability of the core load. The separate cabin type structure can also independently carry out separate cabin thermal decoupling on a single machine of equipment with larger temperature disturbance.

The shell is provided with a radiating surface, and the radiating surface uses a fixed passive radiation radiating mode, namely, the radiating surface uses a high-emissivity coating to discharge waste heat in the star. Specifically, high-emissivity coatings such as white paint can be used in the heat dissipation areas of the outer side wall and the bottom of the shell to discharge heat, so that each single machine in the star is ensured to be in a normal working temperature range.

Preferably, the cooling surfaces are provided on +X outer plate 320, -X +Y outer plate 350, -X outer plate 360, -X-Y outer plate 370 and-Z outer plate 310.

The above embodiments are only for illustrating the technical solution of the present utility model, and not for limiting the same; although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present utility model.

Claims (10)

1. A satellite platform configuration for earth-centered high-orbit space gravitational wave detection, comprising: the sun shield is arranged at the top of the star;

the sun shield comprises a base plate, a sun sensor arranged at the edge position of the top of the base plate, a body-mounted solar cell array arranged at the top of the base plate and a support column connected with the star;

the star comprises a shell with an octagonal right-angle polyhedron structure, a central bearing cylinder arranged at the central position inside the shell, and a plurality of shear walls arranged between the central bearing cylinder and the shell;

the shell divides the star body into a core load cabin, a peripheral load cabin, a platform equipment cabin and a propulsion equipment cabin through the central bearing cylinder and the shear wall.

2. The satellite platform configuration for geocentric high orbit space gravitational wave detection according to claim 1, wherein a core load shield and a movable optical machine assembly are disposed within the core load compartment;

the core load shielding cover is positioned in the central bearing cylinder;

the movable optical machine component is installed in the central bearing cylinder by adopting an integrated structure and is partially nested with the core load shielding cover.

3. The satellite platform configuration for geocentric high orbit space gravitational wave detection according to claim 1, wherein an inertial front-end circuit, a charge management unit, a laser amplifier unit, a scientific load distribution unit, a lock release control unit, an integrated electronics unit and a radiometer are provided within the peripheral load compartment;

wherein the integrated electronic unit and the laser amplifier unit are both mounted on the inner side wall of the housing;

the radiometer is arranged on the outer side wall of the central bearing cylinder;

the inertia front-end circuit, the charge management unit, the laser unit, the scientific load distribution unit and the locking release control unit are all arranged on the shear wall.

4. The satellite platform configuration for geodetic high orbit space gravitational wave detection according to claim 1, wherein the platform equipment compartment is provided with an inter-satellite link antenna, a GNSS receiver, a power control and distribution unit and a transponder;

wherein, the inter-satellite link antenna and the GNSS receiver are both arranged on the inner side wall of the shell;

the power control and distribution unit and the transponder are both mounted on the shear wall.

5. The satellite platform configuration for geocentric high-orbit space gravitational wave detection according to claim 1, wherein an orbit-controlled propulsion control unit, a high-pressure gas cylinder, a star-sensitive circuit unit, a satellite-borne computer, a fiber optic gyroscope and a storage battery pack are arranged in the propulsion equipment cabin;

wherein the fiber optic gyroscope is mounted on the inner side wall of the housing;

the rail-controlled propulsion control unit, the star-sensitive circuit unit, the satellite-borne computer and the storage battery pack are all arranged on the shear wall;

the high-pressure gas cylinder is arranged at the inner bottom of the shell.

6. The satellite platform configuration for geocentric high orbit space gravitational wave detection according to claim 1, wherein said star is further provided with an overhanging means;

the overhanging component comprises a star sensor, a docking ring, a data transmission antenna, a micro propeller and a rail-controlled propeller, wherein the star sensor is arranged on the shell, the docking ring and the data transmission antenna are arranged at the bottom of the shell, and the micro propeller and the rail-controlled propeller are symmetrically arranged on the outer side wall of the shell.

7. The satellite platform configuration for geocentric high orbit space gravitational wave detection according to claim 1, wherein the base plate and the bottom of the housing are each provided with an inter-satellite connection interface for a sampsonii series connection.

8. The satellite platform configuration for geocentric high orbit space gravitational wave detection according to claim 1, wherein said housing, said shear wall and said base plate are each made of carbon fiber composite skin honeycomb structural panels.

9. The satellite platform configuration for geocentric high orbit space gravitational wave detection according to claim 1, wherein the support column is bolted to the base plate and the star, respectively, at both ends;

the support column is made of titanium alloy or aluminum alloy.

10. The satellite platform configuration for geodetic high orbit space gravitational wave detection of claim 1, wherein said housing has a cooling surface disposed thereon.