A high-stability large remote sensing satellite platform

Abstract

The application provides a high-stability large remote sensing satellite platform, which comprises three parts: a bearing cylinder, a platform cabin and a load adapting structure; the platform cabin is non-closed and wrapped outside the bearing cylinder, and the load adapting structure is fixed above the bearing cylinder; the platform cabin is a plate structure, and is not fixedly connected with the load adapting structure; and the bottom of the bearing cylinder is used for connecting a carrier rocket. In the design of the platform, the load adapting structure is directly fixed with the bearing cylinder, the load adapting structure is not connected with other structures of the satellite platform, the force transmission of the whole spacecraft takes the bearing cylinder as the core, and the load generated by the effective load is transmitted to the carrier through the load adapting structure and the bearing cylinder.

Description

Technical Field

[0001] This invention relates to a highly stable large remote sensing satellite platform, belonging to the field of spacecraft overall design technology. Background Technology

[0002] As the accuracy of remote sensing satellites increases, the weight of their payloads also increases, making the need for large remote sensing satellite platforms capable of carrying large remote sensing payloads weighing 1,500 kg to 2,500 kg and with a total satellite weight of 4,000 kg to 8,000 kg increasingly urgent.

[0003] The commonly used main load-bearing structures for existing large remote sensing satellite platforms include load-bearing cylindrical shells, box-type honeycomb panels, and trusses. Among these, box-type structures have relatively low load-bearing capacity, while truss structures have joints that bear significant loads, making them prone to design risks. Load-bearing cylindrical shell structures, on the other hand, offer good strength and stiffness in terms of torsional, bending, and shear resistance, and distribute loads evenly, making them ideal for the high load-bearing requirements of platforms. Furthermore, the interior of the shell facilitates the installation of large propellant tanks. Therefore, existing large remote sensing satellite platforms generally use load-bearing cylindrical shells as their main load-bearing structure. However, existing large remote sensing satellite platforms based on load-bearing cylindrical shells as the main load-bearing structure have the following shortcomings:

[0004] Traditional large remote sensing satellite platforms using load-bearing cylinders as the main load-bearing structure struggle to isolate loads from high-temperature deformation zones. A traditional technical solution for large remote sensing satellite platforms using load-bearing cylinders as the main load-bearing structure is attached. Figure 1 As shown, the system consists of a load-bearing cylinder 101, a platform compartment 102, and an equipment compartment 103. A payload 111 is positioned above the platform. The outer plate 104 of the platform compartment is fixedly connected to the outer plate 105 of the equipment compartment, and the outer plate 105 of the equipment compartment is fixedly connected to the payload 111. The advantage of this configuration is that the load generated by the payload 104 is transferred to the load-bearing cylinder 101 without a large cantilever, allowing it to bear a large load even with a relatively high center of mass. However, the equipment in the platform compartment 102 and the equipment compartment 103 generally requires heat dissipation; therefore, heat dissipation surfaces need to be provided on the outer plates 104 and 105 of the platform compartment and the equipment compartment, as the temperature fluctuates significantly during orbit (temperature range -100℃ to +70℃). It is evident that the platform outer plate 104 and the equipment outer plate 105 will undergo significant thermal deformation in orbit. Since the platform outer plate 104 and the equipment outer plate 105, and the equipment outer plate 105 and the payload 111 are fixedly connected, the significant thermal deformation of the platform outer plate 104 and the equipment outer plate 105 will be directly transmitted to the payload 111. Summary of the Invention

[0005] In view of this, the present invention provides a highly stable large remote sensing satellite platform. In the design of this platform, the load adapter structure is directly fixed to the load-bearing cylinder, and the load adapter structure is not connected to other structures of the satellite platform. The force transmission of the entire spacecraft is centered on the load-bearing cylinder. The load generated by the effective payload passes through the load adapter structure to the load-bearing cylinder and then to the launch vehicle.

[0006] The technical solution of this invention:

[0007] A highly stable large remote sensing satellite platform comprises three parts: a load-bearing cylinder, a platform compartment, and a load adapter structure; wherein the platform compartment is non-enclosed and wrapped around the outside of the load-bearing cylinder, and the load adapter structure is fixed above the load-bearing cylinder; the platform compartment is a plate structure and is not rigidly connected to the load adapter structure, and the bottom of the load-bearing cylinder is used to connect to the launch vehicle.

[0008] The load-adaptive structure mainly consists of a cylindrical shell, main beams, secondary beams, variable cross-section end frames, truss auxiliary beams, and connecting corner pieces. The cylindrical shell is fixed to the variable cross-section end frames, and the load-bearing frame passes through the cylindrical shell and is fixed to the variable cross-section end frames. The cylindrical shell and the load-bearing frame are connected by the connecting corner pieces. A heat insulation pad is provided at the root of the cylindrical shell. The cylindrical shell has a connection interface with the propulsion service module. The load-bearing frame provides installation interfaces for large load equipment and load compartment sections, and the variable cross-section end frames provide installation interfaces for small equipment and supports.

[0009] Furthermore, the cross-sectional periphery of the platform cabin of the present invention is octagonal; the electronic equipment of the satellite platform is installed inside the platform cabin; solar panels are arranged on both sides of the platform cabin; and a relay data transmission antenna can be arranged with an opening at the front or rear of the platform cabin.

[0010] Furthermore, the outer envelope dimension of the platform cabin described in this invention does not exceed a circle with a diameter of 3800 mm.

[0011] Furthermore, the load adaptation structure of the present invention mainly consists of a cylindrical shell, a main beam, a secondary beam, a variable cross-section end frame, a truss auxiliary beam, and connecting corner pieces; wherein, the cylindrical shell is fixed to the variable cross-section end frame, and the load-bearing frame passes through the cylindrical shell and is fixed to the variable cross-section end frame; the cylindrical shell and the load-bearing frame are connected by the connecting corner pieces; the cylindrical shell and the variable cross-section end frame are connected by the connecting corner pieces, and a cylindrical shell root heat insulation pad is provided at the root of the cylindrical shell; the cylindrical shell is provided with a connection interface to the propulsion service compartment, the load-bearing frame provides an installation interface for large load equipment and an interface for load compartment sections, and the variable cross-section end frame provides an installation interface for small equipment and supports.

[0012] Furthermore, the load-adapting structure of the present invention has at least two intersecting I-beams in both the longitudinal and transverse directions, with the intersection point inside the load-bearing cylinder, and the height of the I-beams is not less than 250mm; the height of the cylinder shell of the load-adapting structure is not less than 400mm, the diameter is not less than 2300mm, and the outer envelope dimension of the load-adapting structure does not exceed a circle with a diameter of 3800mm.

[0013] Furthermore, the load-adapting structure described in this invention is a carbon fiber composite material.

[0014] Furthermore, the lower end of the load-bearing cylinder described in this invention is connected to the launch vehicle, and the upper end of the load-bearing cylinder is connected to the load-adapting structure. It is made of carbon fiber composite material and has a diameter of not less than 2300mm.

[0015] Furthermore, the load-bearing cylinder of the present invention adopts a skin stringer structure or a grid structure.

[0016] Beneficial effects:

[0017] First, the load adapter structure of the present invention is directly fixed to the load-bearing cylinder, and the load adapter structure is not connected to other structures of the satellite platform. The force transmission of the entire spacecraft is centered on the load-bearing cylinder. The load generated by the effective payload passes through the load adapter structure to the load-bearing cylinder and then to the launch vehicle.

[0018] Secondly, the platform cabin has an octagonal structure, which allows for a larger layout space inside the cabin. The platform cabin has openings that can be used to install relay data transmission antennas. Through a reasonable structural layout, it can meet the installation requirements of electronic equipment on the satellite platform.

[0019] Third, the load-adaptive structure uses main beams, secondary beams, and variable cross-section end frames to provide interfaces with the effective load. The main beams provide support for the camera, while the secondary beams and truss auxiliary beams provide support for the large support structure, with each beam support reinforcing the others through cross-reinforcement.

[0020] Fourth, the load-bearing structure boasts high overall stiffness and strong load-bearing capacity, with easily expandable load mounting surfaces. Employing a combination of plate-shell-beam components, it leverages the load-bearing advantages of each structural member, resulting in high triaxial stiffness and strength. The normal stiffness depends on the design parameters of the load-bearing frame and the cylindrical shell structure, while the lateral stiffness depends on the design parameters of the variable cross-section end frame, the load-bearing frame, and the cylindrical shell structure. The normal stiffness can be significantly increased by raising the height of the load-bearing frame and the cylindrical shell structure. This efficiently achieves a square-to-round transition structural form.

[0021] Fifth, the load adapter structure is not connected to other structures on the satellite platform. The load adapter structure uses carbon fiber material with a low coefficient of thermal expansion and is precisely temperature controlled to reduce the impact of platform thermal deformation on load measurement accuracy.

[0022] Sixth, the lower end of the load-bearing cylinder of this invention is connected to the launch vehicle, and the upper end of the load-bearing cylinder is connected to the load-adaptive structure. The use of carbon fiber composite material can reduce the structural deformation of the load-bearing cylinder. Attached Figure Description

[0023] Figure 1 The traditional spatial layout of large remote sensing satellite platforms based on load-bearing cylinders as the main load-bearing structure;

[0024] Figure 2 Schematic diagram of the technical solution of the present invention;

[0025] Figure 3 Specific embodiments of the present invention;

[0026] Figure 4 Specific implementation method of load-bearing cylinder;

[0027] Figure 5 Internal layout of the specific implementation method of the load-bearing cylinder;

[0028] Figure 6 Specific implementation method of the platform module;

[0029] Figure 7 Specific implementation methods of the load adaptation structure; Detailed Implementation

[0030] The present invention will now be described in detail with reference to specific accompanying drawings and examples.

[0031] like Figure 2-3 As shown, a highly stable large remote sensing satellite platform includes: a load-bearing cylinder 20, a platform compartment 202, and a load adapter structure 303; wherein the load-bearing cylinder 201, the platform compartment 202, and the load adapter structure 203 are: wherein the platform compartment 202 is non-enclosed and wrapped around the outside of the load-bearing cylinder 201, and the load adapter structure 203 is fixed above the load-bearing cylinder 201; the platform compartment 202 is a plate structure, and it is not fixedly connected to the load adapter structure 203.

[0032] In this embodiment, the satellite platform has a Y-axis dimension of 3330mm, an X-axis dimension of 3360mm, and a lateral dimension within an envelope circle with a diameter of 3800mm. The platform height is 1856mm. The load adapter structure is directly fixed to the load-bearing cylinder and is not connected to other structures on the satellite platform. The force transmission of the entire spacecraft is centered on the load-bearing cylinder. The load generated by the effective payload passes through the load adapter structure to the load-bearing cylinder and then to the launch vehicle.

[0033] The platform pod provides mounting locations and space for platform electronics and the 3025 solar array. To maximize internal layout space within the limited fairing space, the platform pod has an octagonal structure with dimensions as shown. Figure 6As shown. The vast majority of electronic equipment on the satellite platform, such as control subsystems, telemetry and control subsystems, integrated electronic subsystems, power supply subsystems, overall circuitry subsystems, propulsion subsystems, thermal control subsystems, data transmission subsystems, and tracking subsystems, are located in platform compartment 202. Solar panels are located on both sides of the platform compartment. A notch 2021 can be opened at the front or rear of platform compartment 202 to accommodate relay data transmission antennas, etc. The outer envelope of the platform compartment does not exceed a circle with a diameter of 3800 mm.

[0034] The equipment layout follows the principle of modular and centralized arrangement of subsystem equipment. Based on the information flow requirements between equipment and systems, it is impossible for all subsystem equipment to be arranged entirely within their respective functional compartments (e.g., the solar panel drive mechanism and its wiring boxes in the control subsystem need to be arranged according to the solar panel location), but the layout principle still follows the modular compartment arrangement principle as much as possible. Priority is given to the layout of equipment with directional and field-of-view requirements on the satellite surface, and its wiring boxes, power amplifiers, and other equipment are placed nearby. After completing the satellite surface equipment layout, the internal equipment is arranged. First, relatively stable mounting surfaces must be selected for equipment requiring installation and registration accuracy, and its accuracy testing channels must be ensured; the layout of high-frequency equipment should prioritize the rationality of cable connections and ensure its electromagnetic compatibility requirements. For newly developed equipment and equipment with significant modifications, sufficient expansion space should be reserved during layout to facilitate adjustments. High-heat-generating equipment is placed close to the heat dissipation surface, and a large radiation angle coefficient is ensured as much as possible; high-heat-generating and low-heat-generating equipment are arranged alternately; equipment with long-term heat consumption and short-term power consumption can be compensated for by heat pipes. At the same time, the overall satellite's center of mass balancing and the openness of the final assembly process are taken into account to facilitate the disassembly and assembly of instruments and the plugging and unplugging of cables during electrical testing and final assembly.

[0035] The load-bearing structure adopts a combination of a 701 cylindrical shell and an I-beam, such as... Figure 7As shown, the basic structure mainly consists of a cylindrical shell 701, a main beam 702, a secondary beam 703, a variable cross-section end frame 705, a truss auxiliary beam 704, and connecting corner pieces. The lower end of the cylindrical shell provides an interface with the load-bearing cylinder; the main beam, secondary beam, and variable cross-section end frame provide interfaces with the payload. The main beam provides support for the camera, while the secondary beam and truss auxiliary beam provide support for the large support structure, with each beam support reinforcing the others. The longitudinal load of the entire satellite is transferred downwards through the main beam, secondary beam, and variable cross-section end frame to the load-adapter structure cylindrical shell; then downwards through the load-adapter structure cylindrical shell to the load-bearing cylinder, and finally to the launch vehicle through the satellite-rocket docking flange. To improve satellite stability, the load-adapter structure is directly fixed to the load-bearing cylinder and is not connected to other structures on the satellite platform. The load-adapter structure uses carbon fiber material with a low coefficient of thermal expansion and is precisely temperature-controlled to reduce the impact of platform thermal deformation on the accuracy of load measurements. Taking into account factors such as load-bearing capacity and the size of large supports, the load-bearing structure size is 3280mm (X direction) × 2800mm (Y direction) × 450mm (Z direction).

[0036] The load-bearing cylinder is the core component for satellite load-bearing, and the attitude control execution module 3023 is located inside the load-bearing cylinder. A hollow octagonal platform compartment is arranged on the outer wall of the load-bearing cylinder. The lower part of the load-bearing cylinder is connected to the launch vehicle, and the upper part is connected to the load module. The structural dimensions of the load-bearing cylinder are as follows: Figure 4 As shown.

[0037] The attitude control actuators are centrally located above the load-bearing cylinder, and momentum wheels or CMGs are installed inside. The various satellite platform devices are mounted on the structural plate of the platform compartment outside the cylinder. To minimize the impact of the attitude control actuators, such as the CMGs, on the payload, vibration damping and isolation designs are implemented between the attitude control actuators and the load-bearing cylinder. The internal layout of the load-bearing cylinder is as follows: Figure 5 As shown. The lower end of the load-bearing cylinder of the present invention is connected to the launch vehicle, and the upper end of the load-bearing cylinder is connected to the load-adaptive structure. It is made of carbon fiber composite material and has a diameter of not less than 2300mm.

[0038] This invention uses a load-bearing cylinder as the center, with a platform cabin surrounding it. Large remote sensing payloads are mounted on a load-adapting structure. The platform cabin adopts a panel structure, and the load-adapting structure, designed according to the configuration characteristics of ultra-large remote sensing payloads, features multiple staggered I-beams embedded in the cylinder shell. The cylinder shell of the load-adapting structure and the load-bearing cylinder have the same structural diameter, and the lower flange of the load-adapting structure's cylinder shell and the upper flange of the load-bearing cylinder are fixed together with screws. Almost all the space above the load-adapting module is dedicated to the payload installation, thus improving the satellite platform's adaptability to payloads. The satellite's force transmission path is as follows: the gravity of the large remote sensing payload is transferred through the beam structure of the load-adapting structure to the overload-adapting structure's cylinder shell structure, then to the load-bearing cylinder, and finally to the launch vehicle. This meets the load-bearing requirements of large remote sensing satellite equipment.

[0039] The satellite platform of this invention has been verified by static tests. With a total satellite mass of 9000 kg and a center of mass height of 2434 mm (relative to the lower end of the load-bearing cylinder), the platform structure withstood various static test conditions without yielding or instability. The structural performance did not change after the tests, and the load-bearing capacity can meet the strength and stiffness requirements. Therefore, the maximum mass of the entire satellite that the platform structure can withstand is not less than 9000 kg.

[0040] The large remote sensing satellite platform, based on the load-bearing cylinder as the main load-bearing structure, has a platform cabin built around it. This increases the volume of the platform cabin, facilitates the layout of electronic equipment, reduces the platform height, and increases the platform's load-bearing capacity, meeting the launch requirements of large remote sensing satellites carrying heavy remote sensing payloads weighing 1500kg to 2500kg and satellites weighing 4000kg to 8000kg. The platform cabin structural plates are not connected to the load-adapting structure, reducing the impact of large thermal deformation of the platform cabin structural plates on the effective payload. This reduces the thermal deformation at the effective payload mounting surface to 1 / 6 of the original value, significantly improving the platform's thermal stability.

[0041] (1) Effectively eliminate the influence of large thermal deformation of the platform's outer plate on the effective load and improve the platform's thermal stability.

[0042] 1) The load-bearing cylinder and the variable cross-section load adapter structure are directly fixed to the payload. The load-bearing cylinder is located inside the spacecraft. The thermal environment of the spacecraft is very good when it is in orbit, and the temperature variation range is small, so the thermal deformation is small. Since the variable cross-section load adapter structure does not have a large heat dissipation backup, it is not necessary to open a heat dissipation surface on the variable cross-section load adapter structure, which facilitates precise temperature control of the variable cross-section load adapter structure. Therefore, the thermal deformation of the variable cross-section load adapter structure is also small.

[0043] 2) Since the platform compartment is no longer directly connected to the payload, the thermal deformation on the outside of the platform compartment needs to be transmitted to the load-bearing cylinder first, and then to the payload via the load-bearing cylinder. The transmission path is very long, resulting in a smaller thermal deformation that is actually transmitted to the payload. A detailed comparative analysis is as follows:

[0044] For the satellite platform in the specific implementation, the connection between the platform cabin and the variable cross-section load adaptor structure has two states: the platform cabin and the variable cross-section load adaptor structure are rigidly connected, and the platform cabin and the variable cross-section load adaptor structure are not connected. A finite element model was established for comparative analysis, and the analysis conditions and results are shown in Tables 1 and 2, respectively.

[0045] Table 1 analyzes temperature operating conditions.

[0046]

[0047]

[0048] Table 2 Analysis Results

[0049]

[0050] 2. The analysis results show that when the platform cabin and the variable cross-section load adapting structure are not connected, the deformation of the effective load mounting surface is much smaller than the deformation when the two are fixed together. Therefore, the present invention can effectively reduce the impact of large thermal deformation of the platform outer plate on the effective load, reduce the thermal deformation at the effective load mounting surface to 1 / 6 of the original, and significantly improve the thermal stability of the platform.

[0051] (2) Reduce the height of the platform's center of gravity to improve its adaptability to different large remote sensing payloads.

[0052] In traditional large remote sensing platforms based on load-bearing cylinders, the height ratio between the platform compartment and the equipment compartment is approximately 1:1. Considering that propellant is loaded below the equipment compartment, the height of the satellite platform's center of gravity is reduced by at least 1 / 3.

[0053] Specific embodiments of the present invention have been described above. The present invention is not limited to the specific embodiments described above, and those skilled in the art can make various modifications or variations within the scope of the claims, which do not affect the essence of the present invention.

Claims

1. A high-stability large remote sensing satellite platform, comprising three parts: a bearing cylinder, a platform cabin and a load adapting structure; characterized in that, The platform compartment is not enclosed and is wrapped around the outside of the load-bearing cylinder. The load adapter structure is fixed above the load-bearing cylinder. The platform compartment is a plate structure and is not fixedly connected to the load adapter structure. The bottom of the load-bearing cylinder is used to connect to the launch vehicle. The load-adaptive structure mainly consists of a cylindrical shell, main beams, secondary beams, variable cross-section end frames, truss auxiliary beams, and connecting corner pieces. The cylindrical shell is fixed to the variable cross-section end frames, and the load-bearing frame passes through the cylindrical shell and is fixed to the variable cross-section end frames. The cylindrical shell and the load-bearing frame are connected by the connecting corner pieces. A heat insulation pad is provided at the root of the cylindrical shell. The cylindrical shell has a connection interface with the propulsion service compartment. The load-bearing frame provides an installation interface for large load equipment and load compartment sections. The variable cross-section end frames provide installation interfaces for small equipment and supports. The lower end of the cylindrical shell provides an interface with the load-bearing cylinder.

2. The highly stable large remote sensing satellite platform according to claim 1, characterized in that, The platform cabin has an octagonal cross-sectional shape; the platform cabin contains electronic equipment for the satellite platform; solar panels are arranged on both sides of the platform cabin; and a relay data transmission antenna can be arranged with an opening at the front or rear of the platform cabin.

3. The highly stable large remote sensing satellite platform according to claim 1, wherein, The outer envelope of the platform compartment does not exceed the diameter of a circle of 3800 mm.

4. The highly stable large remote sensing satellite platform according to claim 3, wherein, The load-adapting structure has at least two intersecting I-beams in each direction, with the intersection point inside the load-bearing cylinder. The height of the I-beams is not less than 250mm. The height of the cylinder shell of the load-adapting structure is not less than 400mm, the diameter is not less than 2300mm, and the outer envelope dimension of the load-adapting structure does not exceed a circle with a diameter of 3800mm.

5. The highly stable large remote sensing satellite platform according to claim 1 or 4, characterized in that, The load-adaptive structure and load-bearing cylinder are made of carbon fiber composite material.

6. The highly stable large remote sensing satellite platform according to claim 1, wherein, The load-bearing cylinder adopts a skin stringer structure or a grid structure.

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