Agile remote sensing satellite platform configuration

Abstract

The application discloses a kind of agile remote sensing satellite platform configurations, it is related to satellite technical field, including star body, remote sensing equipment, foldable energy acquisition system, energy storage module and control system, foldable energy acquisition system includes deployer, foldable device and flexible solar cell panel, deployer includes bottom plate and multiple side plates, bottom plate is fixed to the side of star body, one end of each side plate is connected with bottom plate by a connecting mechanism, connecting mechanism includes positioning hinge, restraint and pyrotechnics, one end of each side plate is connected with bottom plate by positioning hinge, the two ends of restraint are respectively fixed to the outside of side plate and bottom plate, pyrotechnics is fixed on restraint, flexible solar cell panel is fixed on foldable device, and flexible solar cell panel, energy storage module, remote sensing equipment and pyrotechnics are connected with control system.The agile remote sensing satellite platform configuration has the advantages of light weight and high integration, while reducing the launch cost, improves the remote sensing coverage range.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellites, in particular to an agile remote sensing satellite platform configuration. BACKGROUND

[0002] Agile remote sensing satellites are a kind of high-performance satellites that have developed rapidly in recent years, and are characterized in that the satellite platform has the ability to perform large-range rapid attitude maneuvering around any Euler axis and quickly stabilize, thereby supporting the imaging or other types of remote sensors carried to quickly acquire target information. At present, traditional agile remote sensing satellites at home and abroad are mostly based on large platform configurations, which are high in cost and complex in technology, and there is still a lack of functional payload configuration design suitable for agile remote sensing tasks for light and small commercial satellite platforms. In addition, in order to expand the remote sensing coverage range, the remote sensing satellites of the large platform configuration usually adopt a higher orbit, which significantly increases the launch cost. SUMMARY

[0003] To solve the above technical problems, the present application provides an agile remote sensing satellite platform configuration, which has the advantages of lightweight and high integration, reduces the launch cost, and improves the remote sensing coverage range.

[0004] To achieve the above purpose, the present application provides the following scheme:

[0005] The application provides a kind of agile remote sensing satellite platform configuration, including star body, remote sensing equipment, foldable energy acquisition system, energy storage module and control system, the remote sensing equipment, the energy storage module and control system are all arranged in the star body, the star body is provided with the window for the remote sensing equipment to carry out observation, the foldable energy acquisition system includes deployer, foldable device and flexible solar panel, the deployer includes bottom plate and multiple side plates, the bottom plate is fixed to one side of the star body, one end of each side plate is connected with the bottom plate by a connecting mechanism, the connecting mechanism includes positioning hinge, restraint and explosive, one end of each side plate is connected with the bottom plate by the positioning hinge, two ends of the restraint are respectively fixed to the outside of the side plate and the bottom plate, the explosive is fixed to the restraint, the flexible solar panel is fixed to the foldable device, the flexible solar panel, the energy storage module, the remote sensing equipment and the explosive are connected with the control system;The middle part of the foldable device is fixed to the bottom plate, in initial state, multiple side plates and the bottom plate form a containing cavity for containing the foldable device in folded state, the control system is used to control the explosive to release energy after receiving signal, so that the restraint changes from locking state to separation state, so that the restraint no longer constrains the side plate and the bottom plate, the side plate is unfolded to one side of the bottom plate under the action of the positioning hinge, so that the foldable device loses the constraint of the deployer, the foldable device automatically switches to unfolded state, and the flexible solar panel can be unfolded.

[0006] Preferably, the foldable device includes a plurality of connecting components and a plurality of supporting mechanisms, the foldable device is in rectangular structure when in unfolded state, the extension directions of two opposite sides of the rectangular structure are X direction and Y direction respectively, a plurality of connecting components are sequentially arranged along Y direction, each connecting component includes a plurality of connecting pieces sequentially arranged along X direction, any two adjacent connecting pieces along X direction are connected by a supporting mechanism, any two adjacent connecting pieces along Y direction are connected by a supporting mechanism, two ends of each supporting mechanism are rotatably installed on two connecting pieces, a first elastic member is arranged at the connection between the supporting mechanism and the connecting piece, the first elastic member is used to rotate the supporting mechanism to one side of the connecting piece to switch to unfolded state after the foldable device loses the constraint of the deployer, the flexible solar panel is fixed to all connecting pieces, and one connecting piece at the center is fixed to the middle part of the bottom plate away from the star body.

[0007] Preferably, the supporting mechanism comprises a middle piece and two supporting rods, the two supporting rods are respectively rotatably installed on two sides of the middle piece, a second elastic member is arranged at the connection between the supporting rod and the middle piece, the second elastic member is used to switch the two supporting rods to an unfolded state after the foldable device loses the constraint of the deployer; one end of each of the supporting rods away from the middle piece is rotatably installed on one of the connecting pieces, and the first elastic member is arranged at the connection between the supporting rod and the connecting piece.

[0008] Preferably, the four connecting pieces located at the four corners of the rectangular structure have two first connecting structures, the connecting pieces located on the four sides of the rectangular structure except the connecting pieces at the four corners have three first connecting structures, and the connecting pieces located in the middle of the rectangular structure have four first connecting structures.

[0009] The first connecting structure comprises a first mounting slot, a first fixed shaft, a first rotating block, a first connecting column and a first fixing member, the first mounting slot penetrates through the side surface of the connecting piece and the side of the connecting piece away from the bottom plate, the first fixed shaft is fixedly installed on the connecting piece and located in the first mounting slot, the first rotating block is rotatably sleeved on the first fixed shaft, the first elastic member is a first torsion spring, the first torsion spring is sleeved on the first fixed shaft and located inside the first rotating block, two force arms of the first torsion spring are respectively connected with the first fixed shaft and the first rotating block, one end of the first rotating block away from the connecting piece is fixed with the first connecting column, the axis direction of the first connecting column is perpendicular to the axis direction of the first fixed shaft, one end of the supporting rod away from the middle piece is provided with a first connecting slot, the first connecting column extends into the first connecting slot, and the first fixing member is used to fix the supporting rod and the first connecting column.

[0010] The second connecting structure comprises a second fixing shaft, a second rotating block, a second connecting column and a second fixing piece, the second fixing shaft is fixedly installed on the intermediate piece and located in the second installation slot, the second rotating block is rotatably sleeved on the second fixing shaft, the second elastic piece is a second torsion spring, the second torsion spring is sleeved on the second fixing shaft and located in the second rotating block, two force arms of the second torsion spring are connected with the second fixing shaft and the second rotating block respectively, the second connecting column is fixed to one end of the second rotating block away from the intermediate piece, the axis direction of the second connecting column is perpendicular to the axis direction of the second fixing shaft, a second connecting slot is arranged on one end of the support rod close to the intermediate piece, the second connecting column extends into the second connecting slot, and the second fixing piece is used for fixing the support rod and the second connecting column.

[0011] Preferably, the positioning hinge is a 180-degree positioning hinge.

[0012] Preferably, the middle part of the bottom plate is fixed to one side of the star body through a base.

[0013] Preferably, the two bases of the two foldable energy acquisition systems are fixed to two sides of the star body respectively.

[0014] Preferably, the multi-axis holder is fixed in the star body and connected with the control system, and the multi-axis holder is used to drive the remote sensing device to rotate in the two directions of pitch and yaw.

[0015] Preferably, the multi-axis holder comprises a base, a roll shaft motor, a roll frame, a pitch shaft motor and a pitch frame, the base is fixed in the star body, the roll shaft motor is fixed on the base, the roll frame is fixed on the power output shaft of the roll shaft motor, the pitch shaft motor is fixed on the roll frame, the pitch frame is fixed on the power output shaft of the pitch shaft motor, the remote sensing device is fixed on the pitch frame, the central axis of the power output shaft of the pitch shaft motor is perpendicular to and intersects with the central axis of the power output shaft of the roll shaft motor, and the roll shaft motor and the pitch shaft motor are connected with the control system.

[0016] Preferably, the star body comprises a rectangular frame and six outer plates, the six outer plates are fixed outside six sides of the rectangular frame respectively, and one of the outer plates is provided with the window.

[0017] The present application has the following technical effects relative to the prior art:

[0018] The agile remote sensing satellite platform configuration of the application comprises a star body, a remote sensing device, a foldable energy acquisition system, an energy storage module and a control system, the foldable energy acquisition system comprises a deployer, a foldable device and a flexible solar panel, and the control system is used for controlling the release of energy of the initiating explosive after receiving a signal, and changing the constraint from a locking state to a separation state, so that the constraint of the constraint on the side plate and the bottom plate is removed, the side plate is unfolded to one side of the bottom plate under the action of the positioning hinge, the foldable device loses the constraint of the deployer, the foldable device automatically switches to an unfolded state, and the flexible solar panel can be unfolded, and the flexible solar panel can supply power to the satellite after generating electricity.

[0019] The foldable energy acquisition system in the application is in a folded state under the constraint of the deployer in the initial state, the entire foldable energy acquisition system is in a folded state before launching, the occupied space is small, and the integration is improved; meanwhile, the constraint and constraint release of the deployer are realized by the structure of the constraint and the initiating explosive in the application, compared with the structure of the motor and the transmission device in the prior art, the structure is simplified, and the weight is reduced. It can be seen that the application provides a lightweight and high-integration agile remote sensing satellite platform configuration, which has high attitude maneuvering capability, and the agile remote sensing satellite platform configuration is deployed in a low earth orbit, and due to the high attitude maneuvering capability, the latitude and visual angle blind area of the fixed orbit can be broken through, the problem of limited range of earth remote sensing under the condition of limited orbit maneuvering is solved, the launch cost is reduced, and the remote sensing coverage range is improved. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed in the embodiments. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0021] Figure 1 The structure schematic diagram of the agile remote sensing satellite platform configuration provided by the application is shown in the figure.

[0022] Figure 2 The structure schematic diagram of the rectangular frame and the reinforcing rod in the agile remote sensing satellite platform configuration provided by the application is shown in the figure.

[0023] Figure 3 The structure schematic diagram of the multi-axis holder and the remote sensing device in the agile remote sensing satellite platform configuration provided by the application is shown in the figure.

[0024] Figure 4The first perspective structural view of the constraint part of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the locked state;

[0025] Figure 5 The second perspective structural view of the constraint part of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the locked state;

[0026] Figure 6 The perspective structural view of the constraint part of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the separated state;

[0027] Figure 7 The structural schematic view of the deployer in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state;

[0028] Figure 8 The top view of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state;

[0029] Figure 9 The first perspective structural view of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state;

[0030] Figure 10 The structural schematic view of the connection part of the connecting part with four nodes of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state;

[0031] Figure 11 The structural schematic view of the connection part of the connecting part with four nodes of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state after removing one support rod;

[0032] Figure 12 The structural schematic view of the connection part of the connecting part with three nodes of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state after removing one support rod;

[0033] Figure 13 The structural schematic view of the connection part of the connecting part with two nodes of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state after removing one support rod;

[0034] Figure 14 The bottom view of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state;

[0035] Figure 15 The second perspective structural view of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is in the unfolded state;

[0036] Figure 16 The structure diagram of the connection of the intermediate part in the unfolded state of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is shown in the figure.

[0037] Figure 17 The first three-dimensional structure diagram of the connection of the intermediate part in the unfolded state of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is shown in the figure.

[0038] Figure 18 The second three-dimensional structure diagram of the connection of the intermediate part in the unfolded state of the foldable energy acquisition system in the agile remote sensing satellite platform configuration provided by the present application is shown in the figure.

[0039] The figure mark is explained: 1, star body; 101, rectangular frame; 102, reinforcing rod; 103, outer plate; 2, foldable energy acquisition system; 201, bottom plate; 202, base; 203, side plate; 204, constraint part; 205, first connecting plate; 206, first fixed plate; 207, second connecting plate; 208, second fixed plate; 209, positioning hinge; 2010, connecting part; 2011, intermediate part; 2012, support rod; 2013, first fixed shaft; 2014, first rotating block; 2015, first connecting column; 2016, second mounting groove; 2017, second fixed shaft; 2018, second rotating block; 2019, second connecting column; 2020, second torsional spring; 2021, first fixed part; 2022, second fixed part; 3, base; 4, roll axis motor; 5, roll frame; 6, pitch axis motor; 7, pitch frame; 8, remote sensing equipment. DETAILED DESCRIPTION

[0040] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0041] The purpose of the present application is to provide an agile remote sensing satellite platform configuration, which has the advantages of lightweight and high integration, reduces the launch cost, and improves the remote sensing coverage.

[0042] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail below with reference to the drawings and specific embodiments.

[0043] As Figures 1-18As shown, the embodiment provides a kind of agile remote sensing satellite platform configuration, including star body 1, remote sensing equipment 8, foldable energy acquisition system 2, energy storage module and control system, remote sensing equipment 8, energy storage module and control system are all arranged in star body 1, window for being used for remote sensing equipment 8 to carry out observation is provided on star body 1, foldable energy acquisition system 2 includes deployer, foldable device and flexible solar cell panel, deployer includes bottom plate 201 and multiple side plates 203, bottom plate 201 is fixed to the side of star body 1, the end of each side plate 203 is connected with bottom plate 201 by a connecting mechanism, connecting mechanism includes positioning hinge 209, constraint piece 204 and explosive, the end of each side plate 203 is connected with bottom plate 201 by positioning hinge 209, the two ends of constraint piece 204 are respectively fixed to the outside of side plate 203 and bottom plate 201, explosive is fixed on constraint piece 204, flexible solar cell panel is fixed on foldable device, flexible solar cell panel, energy storage module, remote sensing equipment 8 and explosive are connected with control system;The middle part of foldable device is fixed on bottom plate 201, in initial state, multiple side plates 203 and bottom plate 201 form the accommodation cavity for constraint containing the foldable device of retracted state, control system is used to control explosive to release energy after receiving signal, constraint piece 204 changes from locking state to separation state, so that constraint piece 204 no longer constraints side plate 203 and bottom plate 201, side plate 203 is unfolded to the side of bottom plate 201 under the action of positioning hinge 209, so that foldable device loses the constraint of deployer, foldable device automatically switches to unfolded state, and flexible solar cell panel can be unfolded, flexible solar cell panel can supply power to satellite after power generation, the energy acquisition capacity is improved by setting flexible solar cell panel.

[0044] The foldable energy acquisition system 2 in the embodiment is in the retracted state under the constraint of the deployer in the initial state, the entire foldable energy acquisition system 2 is in the retracted state before launch, occupies a small space, and improves the integration degree.

[0045] The embodiment provides a lightweight and high-integration light and small agile remote sensing satellite platform configuration, which has high attitude maneuvering capability. The agile remote sensing satellite platform configuration is deployed in a low earth orbit. Due to the high attitude maneuvering capability, the latitude and viewing angle blind area of the fixed orbit can be broken through, and the problem of limited remote sensing range under the condition of limited orbit maneuvering is solved. The launch cost is reduced, and the remote sensing coverage range is improved.

[0046] The foldable device comprises a plurality of connecting assemblies and a plurality of supporting mechanisms. The foldable device is in a rectangular structure when in an unfolded state. The extending directions of two opposite sides of the rectangular structure are X direction and Y direction respectively. The connecting assemblies are arranged in sequence along the Y direction. Each connecting assembly comprises a plurality of connecting pieces 2010 arranged in sequence along the X direction. Any two adjacent connecting pieces 2010 along the X direction are connected by a supporting mechanism. Any two adjacent connecting pieces 2010 along the Y direction are connected by a supporting mechanism. The two ends of each supporting mechanism are rotatably installed on two connecting pieces 2010 respectively. A first elastic member is arranged at the connection between the supporting mechanism and the connecting piece 2010. When the foldable device is in a folded state, the first elastic member is deformed and stores energy. The first elastic member is used to release the energy by restoring the deformation when the foldable device loses the constraint of the deployer, so that the supporting mechanism rotates to one side of the connecting piece 2010 to switch to the unfolded state. A flexible solar panel is fixed on all connecting pieces 2010. One connecting piece 2010 at the center is fixed to the middle of the side of the bottom plate 201 away from the star 1.

[0047] The supporting mechanism comprises an intermediate piece 2011 and two supporting rods 2012. The two supporting rods 2012 are rotatably installed on the two sides of the intermediate piece 2011. A second elastic member is arranged at the connection between the supporting rod 2012 and the intermediate piece 2011. When the foldable device is in a folded state, the second elastic member is deformed and stores energy. The second elastic member is used to release the energy by restoring the deformation when the foldable device loses the constraint of the deployer, so that the two supporting rods 2012 switch to the unfolded state. The end of each supporting rod 2012 away from the intermediate piece 2011 is rotatably installed on one connecting piece 2010. A first elastic member is arranged at the connection between the supporting rod 2012 and the connecting piece 2010. When the foldable device is in a folded state, the first elastic member is deformed and stores energy. The first elastic member is used to release the energy by restoring the deformation when the foldable device loses the constraint of the deployer, so that the supporting rod 2012 rotates to one side of the connecting piece 2010 to switch to the unfolded state.

[0048] The four connecting pieces 2010 located at the four corners of the rectangular structure have two first connecting structures. The connecting piece 2010 is a connecting piece 2010 with double nodes. The connecting pieces 2010 located on the four sides of the rectangular structure except the connecting pieces 2010 at the four corners have three first connecting structures. The connecting piece 2010 is a connecting piece 2010 with three nodes. The connecting pieces 2010 located in the middle of the rectangular structure have four first connecting structures. The connecting piece 2010 is a connecting piece 2010 with four nodes.

[0049] The connecting piece 2010 in the embodiment is a rectangular block structure. Two first connecting structures of the connecting piece 2010 with two nodes are arranged on two adjacent sides of the connecting piece 2010 respectively. Three first connecting structures of the connecting piece 2010 with three nodes are arranged on two symmetrical sides and one side between the two symmetrical sides of the connecting piece 2010 respectively. Four first connecting structures of the connecting piece 2010 with four nodes are arranged on four sides of the connecting piece 2010 respectively.

[0050] In the embodiment, four connecting pieces 2010 with two nodes are arranged. Three connecting pieces 2010 with three nodes are arranged on each side of the rectangular structure. Twelve connecting pieces 2010 with three nodes are arranged. Nine connecting pieces 2010 with four nodes are arranged. The connecting piece 2010 with four nodes in the center is fixed to the bottom plate 201.

[0051] The first connecting structure comprises a first mounting slot, a first fixed shaft 2013, a first rotating block 2014, a first connecting column 2015 and a first fixing piece 2021. The first mounting slot penetrates through the side of the connecting piece 2010 and the side of the connecting piece 2010 away from the bottom plate 201. The first fixed shaft 2013 is fixedly installed on the connecting piece 2010 and located in the first mounting slot. The first rotating block 2014 is rotatably sleeved on the first fixed shaft 2013. The first elastic piece is a first torsion spring. The first torsion spring is sleeved on the first fixed shaft 2013 and located inside the first rotating block 2014. Two force arms of the first torsion spring are connected with the first fixed shaft 2013 and the first rotating block 2014 respectively. The first connecting column 2015 is fixed to one end of the first rotating block 2014 away from the connecting piece 2010. The axis direction of the first connecting column 2015 is perpendicular to the axis direction of the first fixed shaft 2013. The first connecting slot is arranged on one end of the supporting rod 2012 away from the middle piece 2011. The first connecting column 2015 extends into the first connecting slot. The first fixing piece 2021 is used for fixing the supporting rod 2012 and the first connecting column 2015. The first fixing piece 2021 in the embodiment is a first fixing pin.

[0052] The second installation groove 2016 is provided on one side of the middle piece 2011 close to the bottom plate 201, and two second connecting structures are respectively installed on two sides of the second installation groove 2016. The second connecting structure comprises a second fixed shaft 2017, a second rotating block 2018, a second connecting column 2019 and a second fixing piece 2022. The second fixed shaft 2017 is fixedly installed on the middle piece 2011 and located in the second installation groove 2016. The second rotating block 2018 is rotatably sleeved on the second fixed shaft 2017. The second elastic member is a second torsion spring 2020. The second torsion spring 2020 is sleeved on the second fixed shaft 2017 and located inside the second rotating block 2018. Two force arms of the second torsion spring 2020 are respectively connected with the second fixed shaft 2017 and the second rotating block 2018. The second connecting column 2019 is fixed to one end of the second rotating block 2018 away from the middle piece 2011. The axis direction of the second connecting column 2019 is perpendicular to the axis direction of the second fixed shaft 2017. The second connecting groove is arranged on one end of the supporting rod 2012 close to the middle piece 2011. The second connecting column 2019 extends into the second connecting groove. The second fixing piece 2022 is used for fixing the supporting rod 2012 and the second connecting column 2019. The second fixing piece 2022 in the embodiment is a second fixing pin.

[0053] In the embodiment, the positioning hinge 209 is a 180-degree positioning hinge. After the constraint piece 204 no longer constrains the side plate 203 and the bottom plate 201, the side plate 203 is unfolded to one side of the bottom plate 201 under the action of the positioning hinge 209, and the side plate 203 and the bottom plate 201 maintain a 180-degree angle.

[0054] In the embodiment, the middle part of the bottom plate 201 is fixed to one side of the star body 1 through the base 202, so that there is a certain gap between the periphery of the bottom plate 201 and the star body 1.

[0055] Specifically, the restraint member 204 is a restraint plate, one end of the restraint plate is fixedly connected with the side plate 203 through a first fixing mechanism, the side plate 203 is externally fixed with a first connecting plate 205 at one end close to the bottom plate 201, the first fixing mechanism comprises a first fixing plate 206 and a plurality of first fixing bolts, one end of the restraint plate is located between the first fixing plate 206 and the first connecting plate 205, each first fixing bolt is used for fixing the first fixing plate 206 and the first connecting plate 205, and then one end of the restraint plate is fixedly clamped between the first fixing plate 206 and the first connecting plate 205. The other end of the restraint plate is connected with the bottom plate 201 through a second fixing mechanism, the bottom plate 201 is fixed with a second connecting plate 207 at one end close to one side of the star body 1 and close to one side plate 203, the second fixing mechanism comprises a second fixing plate 208 and a plurality of second fixing bolts, the other end of the restraint plate is located between the second fixing plate 208 and the second connecting plate 207, each second fixing bolt is used for fixing the second fixing plate 208 and the second connecting plate 207, and then the other end of the restraint plate is fixedly clamped between the second fixing plate 208 and the second connecting plate 207, so that the restraint plate is fixed.

[0056] In the specific embodiment, two foldable energy acquisition systems 2 are arranged, and the bases 202 of the two foldable energy acquisition systems 2 are fixed to the two sides of the star body 1 respectively.

[0057] The embodiment also comprises a multi-axis holder, the multi-axis holder is fixed in the star body 1 and connected with the control system, and the multi-axis holder is used to drive the remote sensing device 8 to rotate in the two directions of pitch and yaw. Specifically, the remote sensing device 8 is a remote sensing camera.

[0058] The multi-axis holder comprises a base 3, a roll shaft motor 4, a roll frame 5, a pitch shaft motor 6 and a pitch frame 7, the base 3 is fixed in the star body 1, the roll shaft motor 4 is fixed on the base 3, the roll frame 5 is fixed on the power output shaft of the roll shaft motor 4, the pitch shaft motor 6 is fixed on the roll frame 5, the pitch frame 7 is fixed on the power output shaft of the pitch shaft motor 6, the remote sensing device 8 is fixed on the pitch frame 7, the central axis of the power output shaft of the pitch shaft motor 6 is perpendicular to and intersects with the central axis of the power output shaft of the roll shaft motor 4, and the roll shaft motor 4 and the pitch shaft motor 6 are connected with the control system.

[0059] The control system controls the movement of the pitch shaft motor 6 and the roll shaft motor 4 to realize the accurate rotation of the multi-axis holder in the two directions of pitch and yaw, so as to drive the remote sensing camera to adjust the pointing direction, expand the ground observation range, and improve the flexibility and response ability of satellite remote sensing.

[0060] Specifically, the power output shaft of the roll shaft motor 4 is connected with the roll frame 5 through a shaft coupling or directly, and the power output shaft of the pitch shaft motor 6 is connected with the pitch frame 7 through a shaft coupling or directly.

[0061] The star body 1 comprises a rectangular frame 101 and six outer plates 103, which are respectively fixed to the outer sides of the six sides of the rectangular frame 101, one of the outer plates 103 is provided with a window, and two bases 202 of the foldable energy acquisition system 2 are respectively fixed to the two symmetrically arranged outer plates 103.

[0062] The rectangular frame 101 in the embodiment is provided with a reinforcing rod 102, both ends of the reinforcing rod 102 are fixed to the rectangular frame 101, thereby improving the strength.

[0063] In the specific embodiment, the support rod 2012, the rectangular frame 101 and the reinforcing rod 102 are all made of carbon fiber material, which has the characteristics of light weight and high rigidity; the outer plate 103, the bottom plate 201, the side plate 203, the connecting piece 2010 and the intermediate piece 2011 are all made of aluminum alloy material or titanium alloy material, thereby reducing the weight of the overall device and further reducing the launch cost.

[0064] It should be noted that the outer plate 103, the bottom plate 201, the side plate 203, the connecting piece 2010 and the intermediate piece 2011 can also be made of other lighter metal materials, but the strength of the metal material needs to be ensured.

[0065] In the specific embodiment, the flexible solar cell panel adopts a polyimide-based thin film photovoltaic material, which has ductility that allows it to withstand bending deformation during repeated folding and unfolding of the foldable device without affecting electrical performance, while maintaining stable photoelectric conversion efficiency, thereby simplifying the design while ensuring the reliability and durability of energy collection.

[0066] Before launching, the plurality of constraint pieces 204 constrain the deployment device, and the plurality of side plates 203 and the bottom plate 201 form a containing cavity for containing the foldable device in the folded state. The folding process of converting the foldable device into the folded state is achieved by manually applying external force, without the need for an additional power source. Specifically, folding is first performed in the X direction, and then folding is performed in the Y direction, so that the foldable device is folded, or folding is first performed in the Y direction, and then folding is performed in the X direction, so that the foldable device is folded, and then each side plate 203 is folded upward, and each side plate 203 and the bottom plate 201 are connected by the constraint piece 204. When the foldable device is in the folded state, the plurality of connecting pieces 2010 are located on the side close to the bottom plate 201, and the plurality of intermediate pieces 2011 are located on the side away from the bottom plate 201.

[0067] After the launching, the ground control center sends a signal of the explosion of the pyrotechnics to the control system, and the control system controls the pyrotechnics to release energy after receiving the signal, so as to change the constraint member 204 from the locked state to the separated state, that is, to blow open the constraint member 204, so that the constraint member 204 no longer constrains the side plate 203 and the bottom plate 201, the side plate 203 is unfolded to one side of the bottom plate 201 under the action of the 180-degree positioning hinge, and the side plate 203 and the bottom plate 201 maintain a 180-degree angle, so that the foldable device loses the constraint of the deployer, the foldable device automatically switches to the unfolded state, and the flexible solar panel can be unfolded.

[0068] The foldable device adopts a passive driving mode, that is, no motor or memory alloy parts are needed, and is composed of the supporting rod 2012, the connecting piece 2010 and the intermediate piece 2011. The passive driving mechanism thereof depends on the preset mechanical elastic potential energy, the first torsional spring integrated at the connecting piece 2010 and the second torsional spring 2020 integrated at the intermediate piece 2011 store energy in the folded state, and when the external constraint is removed, the first torsional spring and the second torsional spring 2020 release energy to drive the foldable device to automatically unfold to the working position.

[0069] The principles and implementation manners of the present application are described by using specific examples in the specification, and the above examples are only used to help understand the method of the present application and its core idea; meanwhile, for those skilled in the art, according to the idea of the present application, the specific implementation manners and application ranges will be changed. In summary, the content of the specification should not be understood as a limitation of the present application.

Claims

1. An agile remote sensing satellite platform configuration, characterized by, The application relates to a star body, a remote sensing device, a foldable energy acquisition system, an energy storage module and a control system, the remote sensing device, the energy storage module and the control system are arranged in the star body, a window for observation by the remote sensing device is arranged on the star body, the foldable energy acquisition system comprises a deployer, a foldable device and a flexible solar cell panel, the deployer comprises a bottom plate and a plurality of side plates, one end of each of the side plates is connected with the bottom plate through a connecting mechanism, the connecting mechanism comprises a positioning hinge, a constraint member and a pyrotechnic device, one end of each of the side plates is connected with the bottom plate through the positioning hinge, the constraint member is fixed to the outside of the side plate and the bottom plate, the pyrotechnic device is fixed to the constraint member, the flexible solar cell panel is fixed to the foldable device, the flexible solar cell panel, the energy storage module, the remote sensing device and the pyrotechnic device are connected with the control system, the middle part of the foldable device is fixed to the bottom plate, in the initial state, a plurality of the side plates and the bottom plate form a containing cavity for containing the foldable device in the folded state, the control system is used for receiving signals and controlling the pyrotechnic device to release energy, so that the constraint member is changed from the locked state to the separated state, the constraint member no longer restricts the side plate and the bottom plate, the side plate is unfolded to one side of the bottom plate under the action of the positioning hinge, the foldable device loses the constraint of the deployer, the foldable device is automatically switched to the unfolded state, and the flexible solar cell panel can be unfolded, the foldable device comprises a plurality of connecting assemblies and a plurality of supporting mechanisms, the foldable device is in a rectangular structure in the unfolded state, the extension directions of two opposite sides of the rectangular structure are the X direction and the Y direction, a plurality of the connecting assemblies are sequentially arranged along the Y direction, each of the connecting assemblies comprises a plurality of connecting pieces sequentially arranged along the X direction, any two adjacent connecting pieces along the X direction are connected through a supporting mechanism, any two adjacent connecting pieces along the Y direction are connected through a supporting mechanism, two ends of each of the supporting mechanisms are rotatably installed on two connecting pieces, a first elastic member is arranged at the connecting position of the supporting mechanism and the connecting piece, the first elastic member is used for rotating the supporting mechanism to one side of the connecting piece to switch to the unfolded state after the foldable device loses the constraint of the deployer, the flexible solar cell panel is fixed to all the connecting pieces, and one connecting piece at the center is fixed to the middle part of the bottom plate away from the star body.

2. The agile remote sensing satellite platform configuration of claim 1, wherein, The support mechanism comprises a middle piece and two support rods, the two support rods are respectively rotatably installed on two sides of the middle piece, a second elastic member is arranged at the connection between the support rod and the middle piece, and the second elastic member is used to switch the two support rods to an unfolded state after the foldable device loses the constraint of the deployer; one end of each support rod away from the middle piece is rotatably installed on a connecting piece, and the first elastic member is arranged at the connection between the support rod and the connecting piece.

3. The agile remote sensing satellite platform configuration of claim 2, wherein, The four connecting pieces located at four corners of the rectangular structure have two first connecting structures, the connecting pieces located on four sides of the rectangular structure except the connecting pieces at the four corners have three first connecting structures, and the connecting pieces located in the middle of the rectangular structure have four first connecting structures. The first connecting structure comprises a first mounting groove, a first fixed shaft, a first rotating block, a first connecting column and a first fixing member, the first mounting groove penetrates through the side surface of the connecting piece and the side of the connecting piece away from the bottom plate, the first fixed shaft is fixedly installed on the connecting piece and located in the first mounting groove, the first rotating block is rotatably sleeved on the first fixed shaft, the first elastic member is a first torsion spring, the first torsion spring is sleeved on the first fixed shaft and located inside the first rotating block, two force arms of the first torsion spring are connected with the first fixed shaft and the first rotating block respectively, one end of the first rotating block away from the connecting piece is fixed with the first connecting column, the axis direction of the first connecting column is perpendicular to the axis direction of the first fixed shaft, one end of the support rod away from the middle piece is provided with a first connecting groove, the first connecting column extends into the first connecting groove, and the first fixing member is used to fix the support rod and the first connecting column. The side of the middle piece close to the bottom plate is provided with a second mounting groove penetrating through two sides thereof, two second connecting structures are respectively installed on two sides of the second mounting groove, the second connecting structure comprises a second fixed shaft, a second rotating block, a second connecting column and a second fixing member, the second fixed shaft is fixedly installed on the middle piece and located in the second mounting groove, the second rotating block is rotatably sleeved on the second fixed shaft, the second elastic member is a second torsion spring, the second torsion spring is sleeved on the second fixed shaft and located inside the second rotating block, two force arms of the second torsion spring are connected with the second fixed shaft and the second rotating block respectively, one end of the second rotating block away from the middle piece is fixed with the second connecting column, the axis direction of the second connecting column is perpendicular to the axis direction of the second fixed shaft, one end of the support rod close to the middle piece is provided with a second connecting groove, the second connecting column extends into the second connecting groove, and the second fixing member is used to fix the support rod and the second connecting column.

4. The agile remote sensing satellite platform configuration of claim 1, wherein, The positioning hinge is a 180-degree positioning hinge.

5. The agile remote sensing satellite platform configuration of claim 1, wherein, The middle part of the bottom plate is fixed to one side of the star body through a base.

6. The agile remote sensing satellite platform configuration of claim 5, wherein, The two foldable energy acquisition systems are fixed on two sides of the star body.

7. The agile remote sensing satellite platform configuration of claim 1, wherein, The multi-axis holder is fixed in the star body and connected with the control system, and is used to drive the remote sensing device to rotate in the directions of pitch and yaw.

8. The agile remote sensing satellite platform configuration of claim 7, wherein, The multi-axis holder comprises a base, a roll shaft motor, a roll frame, a pitch shaft motor and a pitch frame. The base is fixed in the star body. The roll shaft motor is fixed on the base. The roll frame is fixed on the power output shaft of the roll shaft motor. The pitch shaft motor is fixed on the roll frame. The pitch frame is fixed on the power output shaft of the pitch shaft motor. The remote sensing device is fixed on the pitch frame. The central axis of the power output shaft of the pitch shaft motor is perpendicular to and intersects with the central axis of the power output shaft of the roll shaft motor. The roll shaft motor and the pitch shaft motor are connected with the control system.

9. The agile remote sensing satellite platform configuration of claim 1, wherein, The star body comprises a rectangular frame and six outer plates. The six outer plates are respectively fixed on the outer sides of the six sides of the rectangular frame. One of the outer plates is provided with the window.

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