CN115743602A - Satellite platform - Google Patents
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- CN115743602A CN115743602A CN202211188293.1A CN202211188293A CN115743602A CN 115743602 A CN115743602 A CN 115743602A CN 202211188293 A CN202211188293 A CN 202211188293A CN 115743602 A CN115743602 A CN 115743602A
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Abstract
The utility model relates to an aerospace technical field particularly, relates to a satellite platform, including the main part with install in the camera load of main part, the main part includes roof, bottom plate and carbon fiber frame, the roof with the bottom plate is parallel to each other set up, the roof with pass through between the bottom plate carbon fiber frame connects. It is an object of the present application to address at least one of the technical problems involved in the background and to provide a satellite platform.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a satellite platform.
Background
The earth observation optical load needs to be arranged on the earth of the satellite, and along with the higher requirement on the observation precision, the load has larger scale and heavier weight, and the higher adaptability requirement is provided for the existing small satellite configuration.
An agile remote sensing small satellite generally needs to be provided with a high-resolution camera, a large-torque Control Moment Gyroscope (CMG) and a large-capacity storage tank, and the overall volume and weight of the satellite are large. At present, the commonly used small satellite platform has small load bearing capacity, the weight ratio of the satellite platform and a load is higher, the rotational inertia of the whole satellite is large, the rapid maneuvering capacity of the satellite is limited, and the requirement of the new generation of remote sensing small satellite for rapid maneuvering and stable imaging cannot be met.
Disclosure of Invention
It is an object of the present application to address at least one of the technical problems involved in the background and to provide a satellite platform.
In order to achieve the purpose, the following technical scheme is adopted in the application:
the application provides a satellite platform, including the main part with install in the camera load of main part, the main part includes roof, bottom plate and carbon fiber frame, the roof with the bottom plate is parallel to each other setting, the roof with pass through between the bottom plate carbon fiber frame connects.
Optionally, the top plate and the bottom plate are both hexagonal plates, and the carbon fiber frames are installed at the six corners of the hexagonal plates in a one-to-one correspondence manner.
The technical scheme has the beneficial effects that: through making roof and bottom plate be hexagonal plate, make the basic structure of main part be the hexagon, have higher structural stability, volume utilization is high, whole inertia is less, through setting up a plurality of carbon fiber frames, then has improved the self intensity of body.
Optionally, the main body further includes a middle plate disposed parallel to the top plate, the middle plate is located between the top plate and the bottom plate, the carbon fiber frame is disposed between the top plate and the middle plate, the top plate and the middle plate are connected by the carbon fiber frame, the carbon fiber frame is disposed between the middle plate and the bottom plate, and the middle plate and the bottom plate are connected by the carbon fiber frame.
The technical scheme has the beneficial effects that: through setting up the medium plate, improved the structural strength of body self.
Alternatively, a fitting hole through which one end of the camera load is fixed to the middle plate is formed on the top plate.
The technical scheme has the beneficial effects that: like this, camera load can be fixed on the medium plate in the embedding main part, rather than fixing the tip of camera load on the roof, has shortened the holistic length of satellite platform, and this one side has effectively reduced the low frequency vibration response of camera load, and on the other hand lets camera load and body carry out the dynamics decoupling of certain degree, and the mutual influence between the vibration of body and the vibration of camera is favorable to satellite platform's resistance science design.
Optionally, the main body further includes a bearing cylinder and a docking ring, both of which are coaxially disposed with the camera load, the bearing cylinder is located below the middle plate, the docking ring is located below the bottom plate, one end of the bearing cylinder is fixed to the middle plate, and the other end of the bearing cylinder is fixedly connected to the docking ring.
The technical scheme has the beneficial effects that: the bearing cylinder adopts a straight cylinder structure, so that the bearing cylinder is a core bearing part for the satellite to be opened and closed.
Optionally, a plurality of carbon fiber frames uniformly distributed in the circumferential direction of the bearing cylinder are arranged between the middle plate and the bottom plate; and each carbon fiber frame is fixedly connected with the bearing cylinder.
The technical scheme has the beneficial effects that: therefore, the bearing cylinder can intensively bear the camera load and the load on the main body, and the core bearing function of the bearing cylinder is improved.
Optionally, the satellite platform provided in this application embodiment includes a plurality of side plates, each side plate is in the even distribution of camera load's circumference, the side plate with the roof, the medium plate and the bottom plate all are connected, the side plate with carbon fiber frame connects.
Optionally, the satellite platform that this application embodiment provided still includes the truss subassembly, the truss subassembly includes annular flange board and carbon fiber pole, the annular flange board with the coaxial setting of camera load, just the annular flange board is located the outside of camera load, the one end of carbon fiber pole with annular flange board fixed connection, the other end with roof fixed connection.
The technical scheme has the beneficial effects that: the truss assembly is primarily used to support data transmission and communication antennas, which are elevated to avoid the obstruction of the camera load in order to obtain the necessary communication field angle.
Optionally, the truss assembly includes a plurality of the carbon fiber rods, each of the carbon fiber rods is arranged in a circumferential direction of the camera load, each of the carbon fiber rods is sequentially connected end to end, and an included angle is formed between two adjacent carbon fiber rods.
The technical scheme has the beneficial effects that: therefore, a triangular supporting structure is formed between the two adjacent carbon fiber rods and the top plate, and a triangular supporting structure is formed between the two adjacent carbon fiber rods and the annular flange plate, so that more stable support is provided for the annular flange plate and the data transmission and communication antenna on the annular flange plate.
Optionally, the truss assembly further comprises a three-way joint, the three-way joint comprises a connecting plate and two sleeves, one end of each of the two sleeves is fixed on the same side plate surface of the connecting plate, the axial direction of one sleeve is inclined relative to the axial direction of the other sleeve, and the two adjacent carbon fiber rods are matched with the two sleeves in a one-to-one correspondence manner; the truss assembly comprises a plurality of three-way joints, and the annular flange plate and the top plate are both provided with the three-way joints.
The technical scheme has the beneficial effects that: like this, improved firm degree and the stability that carbon fiber pole and annular flange board and roof are connected.
The technical scheme provided by the application can achieve the following beneficial effects:
the utility model provides a satellite platform replaces the connecting plate of pure board-like structure in the past through adopting the carbon fiber frame, connects roof and bottom plate, has effectively reduced the weight of main part, and then reduces satellite platform's weight, reduces satellite platform and the weight ratio of load, reduces whole star's inertia, improves satellite's quick maneuvering ability.
Additional features of the present application and advantages thereof will be set forth in the description which follows, or may be learned by practice of the present application.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings used in the description of the embodiments will be briefly described below. It should be apparent that the drawings in the following description are embodiments of the present application and that other drawings may be derived from those drawings by a person of ordinary skill in the art without inventive step.
FIG. 1 is a schematic perspective view of a portion of an embodiment of a main body according to an embodiment of the present disclosure;
FIG. 2 is a perspective view of one embodiment of a truss assembly according to an embodiment of the present disclosure;
fig. 3 is a schematic partial perspective view of an embodiment of a satellite platform provided in an embodiment of the present application;
fig. 4 is a schematic perspective view of an embodiment of a satellite platform provided in an embodiment of the present application;
fig. 5 is a schematic front view structure diagram of an implementation manner of a satellite platform according to an embodiment of the present disclosure.
Reference numerals:
01-assembly holes; 02-top plate;
03-a carbon fiber framework; 04-middle plate;
05-a bottom plate; 06-bearing cylinder;
07-an annular flange plate; 08-carbon fiber rods;
09-casing; 10-a connecting plate;
11-camera load; 12-a docking ring;
13-solar wing sailboard; 14-an antenna;
15-side plate.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present application. 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.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
As shown in fig. 1 to 5, the present application provides a satellite platform, which includes a main body and a camera load 11 mounted on the main body, wherein the main body includes a top plate 02, a bottom plate 05 and a carbon fiber frame 03, the top plate 02 and the bottom plate 05 are arranged in parallel, and the top plate 02 and the bottom plate 05 are connected by the carbon fiber frame 03.
The main reason for the technical problem of the existing satellite platform is that the existing satellite platform mostly adopts a pure plate type structure, so that the weight of the satellite platform is large. The carbon fiber frame 03 preferably has M55J with excellent comprehensive performance, the weight can be the lightest on the premise of ensuring good structural rigidity and strength, and in order to ensure the connection strength, titanium alloy standard embedded parts (connecting pieces) are embedded at all mounting holes; the satellite platform is also fitted with a solar sail panel 13.
The satellite platform that this application embodiment provided replaces the connecting plate of pure board-like structure in the past through adopting carbon fiber frame 03, connects roof 02 and bottom plate 05, has effectively reduced the weight of main part, and then reduces satellite platform's weight, reduces satellite platform and the weight ratio of load, reduces whole star's inertia, improves the quick mobility ability of satellite.
Optionally, the top plate 02 and the bottom plate 05 are both hexagonal plates, and the carbon fiber frames 03 are installed at six corners of the hexagonal plates in a one-to-one correspondence manner. For hexagonal plate through making roof 02 and bottom plate 05, make the basic structure of main part be the hexagon, have higher structural stability, volume utilization is high, whole inertia is less, through setting up a plurality of carbon fiber frame 03, then has improved the self intensity of body. In the embodiment of the present application, the frame may be a square frame, and preferably, diagonal braces are provided on diagonals of the square frame.
Optionally, the main body further includes a middle plate 04 disposed parallel to the top plate 02, the middle plate 04 is located between the top plate 02 and the bottom plate 05, the carbon fiber frame 03 is disposed between the top plate 02 and the middle plate 04, the top plate 02 and the middle plate 04 are connected by the carbon fiber frame 03, the carbon fiber frame 03 is disposed between the middle plate 04 and the bottom plate 05, and the middle plate 04 and the bottom plate 05 are connected by the carbon fiber frame 03. Through setting up medium plate 04, improved the structural strength of body self. When the top plate 02 and the bottom plate 05 are both hexagonal plates, the middle plate 04 may also be a hexagonal plate.
Alternatively, a fitting hole 01 is formed in the top plate 02, and one end of the camera load 11 is fixed to the middle plate 04 through the fitting hole 01. Like this, camera load 11 can be fixed on medium plate 04 in the embedding main part, and not fix camera load 11's tip on roof 02, has shortened the holistic length of satellite platform, and this one side has effectively reduced the low frequency vibration response of camera load 11, and on the other hand lets camera load 11 and body carry out the dynamics decoupling of certain degree, and the mutual influence between the vibration of body and the vibration of camera is favorable to the anti-mathematical design of satellite platform.
Optionally, the main body further includes a bearing cylinder 06 and a docking ring 12, both of which are coaxially disposed with the camera load 11, the bearing cylinder 06 is located below the middle plate 04, the docking ring 12 is located below the bottom plate 05, one end of the bearing cylinder 06 is fixed to the middle plate 04, and the other end of the bearing cylinder 06 is fixedly connected to the docking ring 12. The bearing cylinder 06 adopts a straight cylinder structure, so that the bearing cylinder 06 is a core bearing part for the satellite to be lifted up and down. The bearing cylinder 06 preferably comprises an upper end frame, an aluminum honeycomb cylinder and a lower end frame, the upper end frame and the lower end frame are made of aluminum alloy, the aluminum honeycomb cylinder is of a carbon fiber skin structure with the thickness of 20mm, the upper end frame is connected with the middle plate 04, the lower end frame is connected with the bottom plate 05, and the side face of the honeycomb cylinder is connected with a carbon fiber frame 03 between the middle plate 04 and the bottom plate 05. The upper part of the bearing cylinder 06 is connected with a camera load 11, the side surface is connected with a satellite carbon fiber frame 03, the bottom part is connected with a butt joint ring 12, and the bearing cylinder 06 is a core bearing part for the satellite to be opened and closed.
Optionally, a plurality of carbon fiber frames 03 uniformly distributed in the circumferential direction of the bearing cylinder 06 are arranged between the middle plate 04 and the bottom plate 05; each carbon fiber frame 03 is fixedly connected with the bearing cylinder 06. Thus, the bearing cylinder 06 can intensively bear the camera load 11 and the load on the main body, and the core bearing function of the bearing cylinder 06 is improved.
Optionally, the satellite platform provided by the embodiment of the present application includes a plurality of side plates 15, each of the side plates 15 is uniformly distributed in the circumferential direction of the camera load 11, the side plate 15 is connected to the top plate 02, the middle plate 04 and the bottom plate 05, and the side plate 15 is connected to the carbon fiber frame 03. In the embodiment of the application, preferably, the top plate 02, the middle plate 04, the bottom plate 05 and each side plate 15 all adopt an aluminum honeycomb plate, the aluminum honeycomb plate has an aluminum core, a skin outside the aluminum core is a 0.3mm thick aluminum alloy thin plate, the thickness of the bottom plate 05 is 40mm, the thickness of the middle plate 04 and the thickness of the top plate 02 are 30mm, and when the top plate 02, the middle plate 04 and the bottom plate 05 are hexagonal plates, the thickness of 6 side plates 15,6 and the thickness of each side plate 15 are both 30mm. Each side plate 15 is provided with a mounting hole, and an aerospace standard embedded part (connecting piece) is arranged in each mounting hole, so that the weight of the structure is reduced, and the design and processing cost is reduced. The top plate 02, the middle plate 04, the bottom plate 05 and the bearing cylinder 06 are key parts for transferring force load, and non-standard integral embedded parts are designed for ensuring connection reliability.
Optionally, the satellite platform that this application embodiment provided still includes the truss subassembly, the truss subassembly includes annular flange plate 07 and carbon fiber pole 08, annular flange plate 07 with 11 coaxial settings of camera load, just annular flange plate 07 is located the outside of camera load 11, carbon fiber pole 08 one end with annular flange plate 07 fixed connection, the other end with roof 02 fixed connection. The truss assembly is primarily used to support the data transmission and communication antenna 14, and to raise the antenna 14 to avoid the obstruction of the camera load 11 in order to obtain the necessary communication field angle. The carbon fiber rod 08 is made of high-strength M55J, and the annular flange plate 07 is an aluminum honeycomb plate of carbon fiber skin.
Optionally, the truss assembly includes a plurality of carbon fiber rods 08, each carbon fiber rod 08 is arranged in the circumferential direction of the camera load 11, each carbon fiber rod 08 is sequentially connected end to end, and an included angle is formed between two adjacent carbon fiber rods 08. Therefore, a triangular supporting structure is formed between the two adjacent carbon fiber rods 08 and the top plate 02, and a triangular supporting structure is formed between the two adjacent carbon fiber rods 08 and the annular flange plate 07, so that more stable support is provided for the annular flange plate 07 and the data transmission and communication antenna on the annular flange plate 07.
Optionally, the truss assembly further comprises a three-way joint, the three-way joint comprises a connecting plate 10 and two sleeves 09, one end of each of the two sleeves 09 is fixed on the same side plate 15 of the connecting plate 10, the axial direction of one sleeve 09 is inclined relative to the axial direction of the other sleeve 09, and two adjacent carbon fiber rods 08 are correspondingly matched with the two sleeves 09 one by one; the truss assembly comprises a plurality of three-way joints, and the three-way joints are arranged on the annular flange plate 07 and the top plate 02. That is to say, one end of each carbon fiber rod 08 is fixed on the annular flange plate 07 through one tee joint, the other end of each carbon fiber rod 08 is fixed on the top plate 02 through another tee joint, the same tee joint is matched with two adjacent carbon fiber rods 08, the tee joints installed on the annular flange plate 07 are connected with the annular flange plate 07 through the connecting plates 10, and the tee joints installed on the top plate 02 are connected with the top plate 02 through the connecting plates 10. In this way, the degree of firmness and stability of the connection of the carbon fiber rods 08 with the annular flange plate 07 and the top plate 02 is improved. The tee joint is preferably made of titanium alloy materials.
In order to better explain the satellite platform provided by the application, the application also provides an application example of the satellite platform. In this application example, both the upper and lower frames may be referred to as carbon fiber frames, the truss assembly is also referred to as a Hexapod truss assembly, and the annular flange plate is also referred to as an upper flange plate. Examples of such applications are as follows:
the conventional satellite has the advantages of compact configuration, high space utilization rate, good operability, low manufacturing cost and the like. However, the load bearing capacity is small, the weight of the satellite platform and the load is higher, the rotational inertia of the whole satellite is large, the rapid maneuvering capacity of the satellite is limited, and the requirement of the new generation of remote sensing small satellite for rapid maneuvering and stable imaging cannot be met.
To solve the above problems, a lightweight configuration suitable for a high-resolution remote sensing small satellite has been developed.
The invention solves the problems that: a light-weight small satellite platform can realize rapid maneuvering and stable imaging of a satellite. Compared with the traditional configuration, the weight of the satellite can be greatly reduced, the weight ratio of the structural subsystem to the whole satellite is less than 20%, and the weight ratio of the load to the whole satellite is more than 50%.
The basic configuration of the satellite is a hexagonal configuration, and the configuration has high structural stability, high volume utilization rate and small integral moment of inertia.
The satellite comprises a satellite body, a camera load, a solar wing sailboard, a butt joint ring and the like. The camera load is installed on a middle partition plate of the satellite in an embedded installation mode, the middle partition plate is directly connected with a satellite bearing cylinder, and the bearing cylinder provides an optimal force transmission path for the camera load. The embedded mounting mode of the load effectively reduces the low-frequency vibration response of the camera load on one hand, and enables the camera load and the satellite body to be dynamically decoupled to a certain degree on the other hand, thereby being beneficial to the anti-mechanics design of the satellite platform.
The satellite structure main body adopts a laminated structure. The device consists of a bearing cylinder, a bottom plate, a top plate, a middle plate, side plates, a lower frame, an upper frame and the like, and the specific structure is decomposed as shown in the following figure. All the subsystem equipment of the satellite platform are basically installed in the box body, and the optimal layout is considered for factors such as thermal control, mechanics, irradiation and electromagnetic environment. Wherein, 5 CMGs in pyramid configuration are arranged on the bottom plate of the box body through a bracket, and a rubber shock absorber is arranged between the bracket and the bottom plate of the box body.
The box plates are all aluminum honeycomb plates, wherein skins are aluminum alloy thin plates with the thickness of 0.3mm, honeycomb cores are aluminum cores, the thickness of the bottom plate is 40mm, the thickness of the middle plate and the top plate is 30mm, and the thickness of 6 side plates is 30mm. All mounting hole built-in fittings all select the space flight standard built-in fitting, lighten structure weight and reduce the design processing cost, and bottom plate and medium plate are connected with a bearing section of thick bamboo, are the key position of transmission power load, in order to guarantee to connect the reliability, all designed non-standard whole built-in fittings.
The upper frame and the lower frame are made of carbon fiber materials, M55J with excellent comprehensive performance is preferably selected, the lightest weight can be achieved on the premise of ensuring good structural rigidity and strength, and titanium alloy standard embedded parts are pre-embedded at all mounting holes in order to ensure the connection strength.
The bearing cylinder assembly adopts a straight cylinder type structure and consists of an upper end frame, an aluminum honeycomb cylinder and a lower end frame, and the bearing cylinder assembly is shown in the following figures. The upper end frame and the lower end frame are made of aluminum alloy, the aluminum honeycomb cylinder is of a carbon fiber skin structure with the thickness of 20mm, the upper end frame is connected with the middle plate of the satellite, the lower end frame is connected with the bottom plate of the satellite, and the side face of the honeycomb cylinder is connected with the lower frame of the satellite. The upper part of the bearing cylinder is connected with a camera load, the side surface of the bearing cylinder is connected with a satellite carbon fiber frame, the bottom of the bearing cylinder is connected with a butt joint ring, and the bearing cylinder is a core bearing part which is opened and closed on the satellite bearing.
The Hexapod truss assembly is primarily used to support data transmission and communication antennas that are elevated to avoid the obstruction of the camera load in order to obtain the necessary communication field angle. The Hexapod truss mainly comprises carbon fiber rods, three-way joints and an upper flange plate. Wherein, the carbon fiber pole material adopts the M55J of high strength, and three way connection selects the titanium alloy material for use, goes up the flange plate and is the aluminium honeycomb panel of carbon fiber covering.
The invention has the main technical effects that:
1) The combined hexagonal box structure of the honeycomb plate, the carbon fiber truss and the bearing cylinder has the characteristics of light weight, high rigidity, strong bearing capacity and simple design and processing;
2) The Hexapod bearing structure of large-span also is the first application on the remote sensing small satellite, and M55J high strength carbon fiber material is all chooseed for use to pole and joint, has light in weight, the span is big, stable good characteristics.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and these modifications or substitutions do not depart from the scope of the technical solutions of the embodiments of the present application.
Claims (10)
1. The satellite platform is characterized by comprising a main body and a camera load arranged on the main body, wherein the main body comprises a top plate, a bottom plate and a carbon fiber frame, the top plate and the bottom plate are arranged in parallel, and the top plate and the bottom plate are connected through the carbon fiber frame.
2. The satellite platform of claim 1, wherein the top plate and the bottom plate are hexagonal plates, and the carbon fiber frames are installed at six corners of the hexagonal plates in a one-to-one correspondence manner.
3. The satellite platform of claim 1 or 2, wherein the body further comprises a middle plate disposed parallel to the top plate, the middle plate being located between the top plate and the bottom plate, the carbon fiber frame being disposed between the top plate and the middle plate, the top plate and the middle plate being connected by the carbon fiber frame, and the carbon fiber frame being disposed between the middle plate and the bottom plate, the middle plate and the bottom plate being connected by the carbon fiber frame.
4. The satellite platform of claim 3, wherein a mounting hole is formed in the top plate, and one end of the camera load is fixed to the middle plate through the mounting hole.
5. The satellite platform of claim 4, wherein the body further comprises a bearing cylinder and a docking ring, both of which are coaxially disposed with the camera load, the bearing cylinder is located below the middle plate, the docking ring is located below the bottom plate, one end of the bearing cylinder is fixed to the middle plate, and the other end of the bearing cylinder is fixedly connected with the docking ring.
6. The satellite platform of claim 5, wherein a plurality of carbon fiber frames are disposed between the middle plate and the bottom plate and are uniformly distributed in the circumferential direction of the bearing cylinders; and each carbon fiber frame is fixedly connected with the bearing cylinder.
7. The satellite platform of claim 6, comprising a plurality of side plates, each side plate being evenly distributed around the circumference of the camera load, the side plates being connected to the top plate, the middle plate, and the bottom plate, the side plates being connected to the carbon fiber frame.
8. The satellite platform of claim 4, further comprising a truss assembly, wherein the truss assembly comprises an annular flange plate and a carbon fiber rod, the annular flange plate is coaxially disposed with the camera load and is located outside the camera load, and one end of the carbon fiber rod is fixedly connected with the annular flange plate and the other end is fixedly connected with the top plate.
9. The satellite platform of claim 8, wherein the truss assembly comprises a plurality of the carbon fiber rods, each of the carbon fiber rods being arranged circumferentially around the camera load, each of the carbon fiber rods being sequentially connected end to end with an included angle formed between two adjacent carbon fiber rods.
10. The satellite platform of claim 9, wherein the truss assembly further comprises a tee joint, the tee joint comprising a connecting plate and two sleeves, each of the two sleeves having one end fixed to the same side of the connecting plate, the axial direction of one sleeve being inclined with respect to the axial direction of the other sleeve, and two adjacent carbon fiber rods being fitted to the two sleeves in a one-to-one correspondence; the truss assembly comprises a plurality of three-way joints, and the annular flange plate and the top plate are both provided with the three-way joints.
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| CN202211188293.1A CN115743602A (en) | 2022-09-28 | 2022-09-28 | Satellite platform |
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| US20180290768A1 (en) * | 2015-10-02 | 2018-10-11 | Airbus Defence And Space Sas | Satellite comprising an optical photography instrument |
| CN106564619A (en) * | 2016-10-28 | 2017-04-19 | 航天东方红卫星有限公司 | Novel commercial remote sensing satellite configuration layout |
| CN108674692A (en) * | 2018-04-04 | 2018-10-19 | 南京理工大学 | A kind of remote sensing microsatellite |
| CN111891393A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Hybrid propulsion cabin of small high-orbit satellite common platform |
| CN114408215A (en) * | 2021-12-27 | 2022-04-29 | 航天东方红卫星有限公司 | Satellite configuration suitable for quick maneuvering ultrastable imaging |
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