CN-121990178-A - Remote retrograde orbit satellite load layout structure and satellite assembly

CN121990178ACN 121990178 ACN121990178 ACN 121990178ACN-121990178-A

Abstract

The invention relates to a remote retrograde orbit satellite load layout structure and a satellite assembly, wherein the remote retrograde orbit satellite load layout structure comprises a satellite body, a satellite-borne atomic clock, a satellite-ground or inter-satellite link measurement and communication load, a space observation camera, a laser communication test load, a laser ranging time difference measurement load and a space science detection load, wherein the satellite-borne atomic clock is installed on the inner side surface of the satellite body in a heat conduction way; the satellite-ground or inter-satellite link measurement and communication load comprises an intra-satellite emission component and an extra-satellite antenna, wherein the intra-satellite emission component is installed on the inner side surface of the satellite body in a heat conduction way, the extra-satellite antenna is installed on the outer side surface of the satellite body in a heat insulation way, the space observation camera is installed on the outer side surface of the satellite body in a heat insulation way, the laser communication test load is installed on the inner side surface and the outer side surface of the satellite body, the laser ranging time difference measurement load is installed on the inner side surface of the satellite body in a heat conduction way, and the space science detection load is installed on the inner side surface and the outer side surface of the satellite body. Through reasonable load layout, low-energy-consumption orbit entering of the DRO satellite can be realized.

Inventors

GUAN HONGFEI
SHAO CAIYUN
SHENG QIANG
YANG SHANZHOU
ZHANG FEI
LIU RONGHUI

Assignees

中国科学院空间应用工程与技术中心

Dates

Publication Date: 20260508
Application Date: 20260309

Claims (10)

1. A remote retrograde orbit satellite load layout structure is characterized by comprising a satellite body, a satellite-borne atomic clock, a satellite-ground or inter-satellite link measurement and communication load, a space observation camera, a laser communication test load, a laser ranging time difference measurement load and a space science detection load, wherein the satellite-borne atomic clock is installed on the inner side surface of the satellite body in a heat conducting mode, the satellite-ground or inter-satellite link measurement and communication load comprises an intra-satellite emission component and an extra-satellite antenna, the intra-satellite emission component is installed on the inner side surface of the satellite body in a heat conducting mode, the extra-satellite antenna is installed on the outer side surface of the satellite body in a heat conducting mode, the space observation camera is installed on the outer side surface of the satellite body in a heat conducting mode, a part of the laser communication test load is installed on the outer side surface of the satellite body in a heat conducting mode, a part of the laser ranging time difference measurement load is installed on the inner side surface of the satellite body in a heat conducting mode, and a part of the space science detection load is installed on the inner side surface of the satellite body in a heat conducting mode.
2. The remote retrograde orbit satellite load layout structure according to claim 1, wherein the satellite-borne atomic clock comprises a hydrogen clock, a first rubidium clock and a second rubidium clock, and the hydrogen clock, the first rubidium clock and the second rubidium clock are all installed on the inner side surface of the-Y plate of the satellite body through heat conduction of screws.
3. The remote retrograde orbit satellite load layout structure according to claim 1, wherein the intra-satellite transmitting assembly comprises a transmitter, a processor, a power amplifier and a microwave network, the transmitter, the processor and the power amplifier are respectively installed on the inner side surface of a +Z plate of a satellite body in a heat conducting manner through screws, the microwave network is installed on the inner side surface of a +Z plate of the satellite body in a heat conducting manner through screws, the extra-satellite antenna comprises a K load 0.6m caliber antenna, a K load 0.22m caliber antenna and a K load quasi-omni antenna, the K load 0.6m caliber antenna and the K load 0.22m caliber antenna are installed on the outer side surface of the +Z plate of the satellite body in a heat insulating manner, and the K load quasi-omni antenna is installed on the outer side surface of the +X plate of the satellite body in a heat insulating manner.
4. The remote retrograde orbit satellite load layout structure according to claim 1, wherein the laser communication test load comprises an optical machine main body, an optical machine electric control box and a signal processor, the optical machine main body is installed on the outer side face of the +z plate of the satellite main body in a heat-insulating way, and the optical machine electric control box and the signal processor are installed on the inner side face of the-Y plate of the satellite main body in a heat-conducting way through screws.
5. The remote retrograde orbit satellite load layout structure according to claim 1, wherein the laser ranging time difference measurement load comprises a laser time difference measuring instrument, a passive laser corner reflector and a laser corner reflecting shade, the laser time difference measuring instrument is installed on the inner side surface of the +z plate of the satellite body in a heat conduction manner through a screw, the passive laser corner reflector is installed on the outer side surface of the +z plate of the satellite body in a heat insulation manner, and the laser corner reflecting shade is installed on the outer side surface of the +z plate of the satellite body in a heat insulation manner and is shielded on the outer side of the passive laser corner reflector.
6. The remote retrograde orbit satellite load layout structure according to claim 1, wherein the space science detection load comprises a GTM electric cabinet and a plurality of GTP probes, the GTM electric cabinet is installed on the inner side surface of the +y plate of the satellite body in a heat conduction manner through screws, and the GTP probes are installed on the outer side surface of the satellite body in a heat insulation manner respectively.
7. The remote retrograde orbit satellite load layout structure according to claim 6, wherein at least one GTP probe is installed on the outer side of the-Z plate, -X plate, -Y plate and +y plate of the satellite body in a heat-insulating manner.
8. The remote retrograde orbit satellite load layout structure according to claim 1, wherein the heat insulation installation comprises heat insulation installation by using a glass fiber reinforced plastic heat insulation pad, and a heat pipe for heat dissipation is arranged on the inner side surface of the satellite body.
9. A satellite assembly comprising a remote retrograde orbit satellite load configuration according to any one of claims 1 to 8, and further comprising cruising satellites; the launching stage is that the +X plate of the cruising satellite is connected with the outer side surface of the +X plate of the satellite body through a satellite and rocket separation assembly; In the orbit entering stage, the cruising satellite is separated from the satellite body, the remote retrograde orbit satellite enters the DRO orbit, the cruising satellite enters the RO orbit, the outer side surface of the +Z plate of the satellite body is opposite to the ground, and the outer side surface of the +Z plate of the cruising satellite is opposite to the ground.
10. The satellite assembly of claim 9, further comprising LEO satellites, the LEO satellites entering sun-synchronous orbit during an in-orbit phase, the +z plate of the LEO satellites pointing toward the satellite body.

Description

Remote retrograde orbit satellite load layout structure and satellite assembly Technical Field The invention relates to the technical field of satellite correlation, in particular to a remote retrograde orbit satellite load layout structure and a satellite assembly. Background The DRO exploration research is one of strategic lead technology special items, realizes DRO low-energy in-orbit and long-term stable berthing, verifies DRO-based autonomous cruising ability of the DRO-based wide-area flight, and performs strategic lead effects for implementing DRO-based gamma ray exploration research and the like. The DRO engineering development comprises three small satellites (DRO satellites, cruising satellites and LEO satellites) and 10 remainder loads, wherein the sum of the masses of the A star (DRO satellite) and the B star (cruising satellite) is not more than 600kg, the final value is matched with the carrier rocket capacity, and the mass of the L star (LEO satellite) is not more than 120kg. According to task targets, task indexes, a task overall scheme and full consideration of rocket carrying capacity constraint, an A star (320 kg, DRO) and a B star (275 kg, ground-month space resonance orbit) are launched by the one-rocket-two-star combination, the carrying application load mass is not more than 104.6kg, and the L star (120 kg, LEO) carrying application load mass is about 35kg. The load on the three small satellites aims at supporting the functional requirements of inter-satellite link construction, inter-satellite communication measurement, autonomous orbit determination of the space base, autonomous cruising of wide-area flight and the like of the three satellites in the earth-moon space and supporting the development of space scientific detection by utilizing the earth-moon space, so that the requirements of heat dissipation, weight and link construction and the like are required to be considered in the satellite load layout. Disclosure of Invention The invention provides a remote retrograde orbit satellite load layout structure and a satellite assembly for solving one or more technical problems in the prior art. The technical scheme includes that the remote retrograde orbit satellite load layout structure comprises a satellite body, a satellite-borne atomic clock, a satellite-ground or inter-satellite link measurement and communication load, a space observation camera, a laser communication test load, a laser ranging time difference measurement load and a space science detection load, wherein the satellite-borne atomic clock is installed on the inner side surface of the satellite body in a heat conducting mode, the satellite-ground or inter-satellite link measurement and communication load comprises an intra-satellite emission component and an extra-satellite antenna, the intra-satellite emission component is installed on the inner side surface of the satellite body in a heat conducting mode, the extra-satellite antenna is installed on the outer side surface of the satellite body in a heat conducting mode, the space observation camera is installed on the outer side surface of the satellite body in a heat conducting mode, part of the laser communication test load is installed on the outer side surface of the satellite body in a heat conducting mode, the other part of the laser communication test load is installed on the inner side surface of the satellite body in a heat conducting mode, the other part of the space science detection load is installed on the inner side surface of the satellite body in a heat conducting mode. The remote retrograde orbit satellite load layout structure has the beneficial effects that the weight requirement of a DRO satellite (namely the remote retrograde orbit satellite) can be met through reasonable load layout, the low-energy-consumption orbit entering of the DRO satellite is realized, the ground-month space entering cost is obviously reduced, and a new path is opened up for large-scale month space development and utilization. The invention is also beneficial to constructing a large-scale satellite constellation in earth-moon space so as to be convenient for exploring the unique property and application value of the remote retrograde orbit. The load layout structure of the remote retrograde orbit satellite, namely the remote retrograde orbit satellite, disclosed by the invention, has the advantages that the load layout is required to meet the heat dissipation requirement, the loads of the same type are nearby, the cable paths connected with each other are shortened, and the weight of the satellite is reduced. On the basis of the technical scheme, the invention can be improved as follows. Further, the satellite-borne atomic clock comprises a hydrogen clock, a first rubidium clock and a second rubidium clock, wherein the hydrogen clock, the first rubidium clock and the second rubidium clock are installed on the inner side face of the-Y plate of the satellite body in a heat