Stacked optical remote sensing satellite platform

Abstract

A stackable optical remote sensing satellite platform disclosed by the present invention comprises a satellite main body structure, two folding satellite solar wings and a stackable pressing and releasing device, the satellite main body structure comprises an upper structural plate, a lower structural plate and two partition plates, the upper structural plate and the lower structural plate are similar in shape and parallel in position, and the two partition plates are arranged on the upper structural plate and the lower structural plate. Each partition plate is perpendicular to and connected with the opposite faces of the upper structural plate and the lower structural plate to jointly form a three-dimensional space, and the foldable satellite solar wing is installed on a satellite main body structure through a solar wing pressing and releasing device in the satellite launching stage and provides energy for a satellite after being unfolded in orbit. And the stacked pressing and releasing device is mounted on the satellite main body structure and is used for pressing the combination formed by the multiple satellites during stacked launching and releasing the combination formed by the multiple satellites during on-orbit satellite-rocket separation. According to the invention, the space of the fairing of the carrier rocket can be fully utilized, and low-cost stacked launching and orbit injection of the very-high-resolution optical remote sensing satellite are realized.

Description

Technical Field

[0001] The invention relates to a stacked optical remote sensing satellite platform, belonging to the field of satellite platform development. Background Art

[0002] The large-scale application of optical remote sensing satellites has directly promoted the construction of optical remote sensing satellite constellations. Traditional optical remote sensing satellite platforms adopt a design and construction model that combines a cabin structure with a subsystem. Each subsystem is composed of different stand-alone devices or functional modules. The advantage of this design is that the satellite platform is highly versatile. For different mission requirements, the satellite platform only needs to make a small amount of adaptive modifications, which can shorten the satellite development cycle. The disadvantage is that the platform has low integration, the size and weight of the entire satellite are large, and the satellite launch must adopt a one-satellite-per-rocket launch method, or a one-satellite-per-rocket launch method based on multiple satellites in parallel or series, resulting in low utilization of carrier rocket resources and high launch costs, which in turn affects the construction of constellation networks.

[0003] Sun Wei and others from the Shanghai Satellite Engineering Research Institute published a paper titled "Research on the Design of Agile Optical Satellite Structure Based on Platform and Payload Integration" in the first issue of Volume 39 of Guidance and Fuze. They designed a satellite structure based on platform and payload integration, which to a certain extent compressed the scale of the entire satellite and reduced the mass and volume of the entire satellite. However, the interface design between the satellite platform and the carrier is still the traditional satellite-rocket connection ring, which cannot be launched in large quantities at low cost.

[0004] The Chinese patent application number CN116424570A, entitled "A foldable and unfoldable stacked satellite configuration for launching multiple satellites with one rocket", discloses a stackable satellite configuration and a launch support method thereof. The patent can achieve efficient stacking of satellites during launch, but the satellite configuration has the following main problems:

[0005] It is mainly limited to flat-panel satellites that are easy to stack. In order to improve imaging quality, optical remote sensing satellites usually choose large-aperture, long-focal-length optical systems. The entire satellite has a non-flat structure, which makes it impossible to adopt the stacking configuration described in this patent and to fully utilize the space of the launch vehicle fairing.

[0006] In summary, this satellite configuration can be applied to stacked satellites such as communications, but is not suitable for optical remote sensing satellites. Summary of the invention

[0007] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and provide a stacked optical remote sensing satellite platform, which can fully utilize the space of the carrier rocket fairing and realize the low-cost stacked launch of very high-resolution optical remote sensing satellites into orbit.

[0008] The technical solution of the present invention is: a stacked optical remote sensing satellite platform, including: a satellite main structure, two foldable satellite solar wings and a stacked compression release device, wherein:

[0009] The satellite main structure includes: an upper structural plate, a lower structural plate and two partitions, wherein: the upper structural plate and the lower structural plate have the same shape and are parallel in position, and each partition vertically connects the opposite surfaces of the upper structural plate and the lower structural plate to form a three-dimensional space together;

[0010] Foldable satellite solar panels are installed on the satellite's main structure through a solar panel compression and release device during the satellite launch phase, and provide energy for the satellite after being unfolded in orbit;

[0011] The stacking compression and release device is installed on the main structure of the satellite. It is used to compress the combination formed by multiple satellites during stacking launch, and to release the combination formed by multiple satellites during in-orbit satellite-rocket separation.

[0012] Preferably, the top view projection of the satellite main structure configuration is in the shape of an upper structural plate, which is a symmetrical polygon;

[0013] The main structure of the satellite is a flat box-type structure as a whole, which can carry a foldable optical payload camera. The height of the main structure of the satellite is the same as the height of the foldable optical payload camera after it is folded. There is a hole in the center of the upper structure plate, and part of the structure of the foldable optical payload camera can extend out from the hole in the upper structure plate. The lower structure plate is a complete structure plate, and the foldable optical payload camera is installed on the inner surface of the lower structure plate.

[0014] Preferably, before being deployed in orbit, the two foldable satellite solar wings are folded and pressed against the upper structural plate or the lower structural plate of the satellite main structure.

[0015] Preferably, the foldable satellite solar wing is a circular deployable structure, including: a fixing rod, a support rib assembly, a root hinge, an unfolding drive mechanism, a solar blanket, and a solar cell sheet; specifically:

[0016] The fixing rod is connected to the satellite main structure through a hinge at the root, and the other end is connected to the deployment drive mechanism; the support rib assembly includes a plurality of support ribs, one end of each support rib is connected to the deployment drive mechanism, and the other end is suspended in the air, the solar blanket is attached to the support ribs of the support rib assembly, and the solar cells are distributed on the solar blanket;

[0017] In the unfolded state, the support rib assembly is radially centered on the unfolding drive mechanism, and the solar blanket is spread on the support rib assembly. In the folded state, the support rib assembly is parallel to the fixing rod, and the solar blanket folds along with the state of the support rib assembly.

[0018] Preferably, the foldable satellite solar wing is in a folded state when the satellite is launched, and is folded and pressed against the edge of the satellite's main structure by a solar wing pressing and releasing device; after the satellite enters orbit, the solar wing pressing and releasing device is released, and the fixing rod moves to a predetermined position through a root hinge, and then the support rib assembly, driven by the unfolding drive mechanism, drives the solar blanket to gradually unfold around the central unfolding mechanism to form a circular surface.

[0019] Preferably, each satellite platform is equipped with two foldable satellite solar wings, and each foldable satellite solar wing uses a triple-junction gallium arsenide solar cell sheet with an efficiency of 32%±2%, a sheet efficiency of 80%±5%, a single-wing output power better than 950 watts, and a double-wing output power better than 1900 watts.

[0020] Preferably, each stacked compression release device comprises a compression connection column, a locking column, and a compression connection separation spring; wherein: the compression connection column is installed on the satellite main structure parallel to the vertical side of the partition;

[0021] During the docking process between the multiple satellite platforms and the clamping device, the multiple satellite platforms are aligned through the positioning grooves on the clamping connection column, the locking column is installed in the guide grooves of all the clamping connection columns of the multiple satellite platform assembly, the bottom locking column is connected to the launch vehicle adapter through a hinge, and at the same time, a pre-tightening force is applied to the top locking column in the direction of the multiple satellite platform assembly to press the clamping connection columns of each satellite platform, thereby realizing a clamped and fixed connection between the multiple satellite platform assembly and the launch vehicle;

[0022] The compression connection separation spring is adjacent to the compression connection seat and is arranged on the lower surface of the lower structural plate of each satellite platform; after multiple satellites are docked and compressed, the upper structural plate of the lower satellite platform and the lower structural plate of the upper satellite platform put the separation spring in a compressed state to store elastic potential energy; after the satellite enters orbit, the preload force at the top of the locking column is released and expanded 45±5° to ensure safe separation of the satellites.

[0023] Preferably, the stacked compression release device adopts a point-type connection compression unlocking device and a point-type connection separation spring, specifically:

[0024] When the satellite platform is in a non-stacked state, the upper flange of the point-connected clamping and unlocking device is installed at the four corners of the lower surface of the lower structural plate of the satellite platform. The satellite platform that has been installed with the point-connected clamping and unlocking device is installed on the upper surface of the upper structural plate of the lower satellite platform through the lower flange of the point-connected clamping and unlocking device. After repeated installation, a multi-satellite stacking launch assembly is formed; the point-connected separation spring is installed at an adjacent position of the point-connected clamping and unlocking device.

[0025] After the satellite is launched into orbit, the point-connected compression and unlocking devices from top to bottom are powered and unlocked in turn, and the corresponding satellite platforms are ejected in turn under the action of their own point-connected separation springs to achieve separation.

[0026] Preferably, the three-dimensional space formed by the upper structural plate, the lower structural plate and the two partitions in the satellite main structure can also be loaded with electronic and mechanical equipment including power supply and distribution, integrated data management, communication, and attitude control functions.

[0027] Compared with the prior art, the present invention has the following advantages:

[0028] The present invention designs an optical remote sensing satellite stacking technology for a foldable optical payload camera, which can solve the problem that optical remote sensing satellites cannot adopt a stacked configuration, make full use of the space of the carrier rocket fairing, greatly increase the number of optical remote sensing satellites carried by the carrier rocket in one launch, and improve the utilization rate of the carrier rocket resources. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 A schematic diagram of a stacked optical remote sensing satellite platform when folded provided by an embodiment of the present invention;

[0030] Figure 2 A schematic diagram of the structure of a satellite platform provided by an embodiment of the present invention;

[0031] Figure 3 A schematic diagram of the configuration of a satellite platform provided by an embodiment of the present invention when deployed;

[0032] Figure 4 A schematic diagram of the configuration of a solar wing when unfolded provided by an embodiment of the present invention;

[0033] Figure 5 A schematic diagram of the configuration of multiple satellite platforms provided in an embodiment of the present invention when stacked in an integrally connected, compressed and released manner;

[0034] Figure 6 A schematic diagram of the configuration of multiple satellite platforms provided in an embodiment of the present invention when stacked in a point-type connection, compression and unlocking form. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solution and advantages of the present invention more clear, the technical solution in the embodiment of the present invention will be clearly and completely described below in conjunction with an embodiment of the present invention and the drawings in the embodiment.

[0036] like Figure 1 As shown, a schematic diagram of a stacked optical remote sensing satellite platform when folded is provided in an embodiment of the present invention, wherein the stacked optical remote sensing satellite platform configuration 1 includes:

[0037] The satellite main structure includes an upper structure plate 10, a lower structure plate 20 and two partitions 30, wherein: the upper structure plate 10 and the lower structure plate 20 are similar in shape, parallel in position, and have a size of 1800mmX1500mm; a hole is opened in the center of the upper structure plate, and a camera secondary mirror support mechanism extends from the opening of the upper structure plate; each partition is perpendicular to and connects the opposite surfaces of the upper structure plate 10 and the lower structure plate 20 to form a three-dimensional space for loading a foldable optical payload camera 40, as well as electronic and mechanical equipment including power supply and distribution, integrated data management, communication, attitude control and other functions;

[0038] The foldable satellite solar wing 50 is installed in the satellite launch phase through the solar wing compression release device. Figure 2 The long oblique sides 101 / 102 / 201 / 202 of the upper and lower structural plates of the satellite main structure shown provide energy for the satellite after being deployed in orbit;

[0039] The stacking compression and release device 60 is installed on the upper and lower structural plate sides 103 / 203 of the satellite main structure and the two partition plate sides 301 / 302 by screws. It is used to compress the combination formed by multiple satellites during stacking launch and to release the combination formed by multiple satellites during in-orbit satellite-rocket separation.

[0040] for Figure 2 In the technical solution shown, the satellite main structure configuration is designed to be in the shape of the upper structure plate 10 when viewed from above. It is a symmetrical polygon that is approximately trapezoidal in shape. The axis of symmetry is parallel to the direction of the partition 30, and the upper and lower sides are perpendicular to the axis of symmetry. The shape of the lower structure plate 20 is consistent with that of the upper structure plate 10; the height direction is a flat box-like structure as a whole. The height of the satellite main structure is the same as the height of the folded optical payload camera 40; the lower structure plate is a complete structure plate, and the folded optical payload camera 40 is installed on the inner surface of the lower structure plate; the upper structure plate has a hole in the center, and the camera secondary mirror support mechanism extends from the hole in the upper structure plate. The two solar wings are folded and pressed against the two long hypotenuses 101 / 102 / 201 / 202 of the upper and lower structure plates of the satellite main structure, respectively, and the length of the hypotenuse of the satellite configuration matches the length of the solar wings.

[0041] The long oblique sides 101 / 102 / 201 / 202 of the upper and lower structural plates can be configured with foldable satellite solar wings with a larger radius, while allowing the satellite solar wings to fit more closely with the satellite main structure when folded, while taking into account the full utilization of the cross-sectional area of ​​the launch fairing; the flat box-type structure minimizes the longitudinal size of the satellite to accommodate the longitudinal stacking of multiple satellites along the fairing, thereby making full use of the envelope space of the launch vehicle and achieving the optimal number of launches. Therefore, compared with the traditional launch mode, it has a higher launch efficiency.

[0042] It should be noted that only the basic configuration of the stacked optical remote sensing satellite platform is shown in the embodiment of the present invention. In the specific implementation process, other components can be configured according to the actual mission requirements, such as antennas required for communication, sensors required for attitude measurement, thrusters required for orbit control, etc. In order to maintain the stacked configuration of the satellite platform and reduce the height of the satellite platform, the communication antenna can use a microstrip antenna or a phased array antenna, and each component can be arranged on the structural edge of the satellite body where the satellite solar wing is not installed.

[0043] On the other hand, in the embodiment of the present invention, the electronic and mechanical equipment of the satellite is mainly installed in the three-dimensional space formed by the main structure. In the specific implementation process, in order to improve the commonality of the satellite platform and different payload interfaces and reduce the volume, weight and power consumption of the equipment, the electronic equipment can adopt a modular design to integrate multiple functional modules in a common chassis, and the mechanical equipment can adopt micro-electromechanical technology.

[0044] The foldable satellite component used in the embodiment of the present invention includes a foldable satellite solar wing 50 and a foldable optical payload camera 40. After the foldable satellite solar wing 50 and the foldable optical payload camera 40 are unfolded in orbit, Figure 3 shown.

[0045] The foldable satellite solar wing 50 adopts a circular deployable structure. Figure 4 As shown. The satellite solar wing is composed of a fixing rod 501, a supporting rib assembly 502, a root hinge 503, an unfolding driving mechanism 504, a solar blanket 505, and a solar cell sheet. The fixing rod 501 is connected to the root hinge 503, the supporting rib assembly 502 is connected to the fixing rod 501 through the unfolding driving mechanism 504, and the solar blanket 505 is connected to the supporting rib assembly 502. The fixing rod 501 is connected to the satellite main structure through a hinge 503 at the root, and the other end is connected to the unfolding drive mechanism 504; the support rib assembly 502 includes a plurality of support ribs, one end of each support rib is connected to the unfolding drive mechanism 504, and the other end is suspended, the solar blanket 505 is connected to the support ribs of the support rib assembly 502, and the solar cells are distributed on the solar blanket 505; in the unfolded state, the support rib assembly 502 is radial with the unfolding drive mechanism 504 as the center, and the solar blanket 505 is spread on the support rib assembly 502, and in the folded state, the support rib assembly 502 is parallel to the fixing rod 501, and the solar blanket 505 is folded according to the state of the support rib assembly 502.

[0046] The foldable satellite solar wing 50 is in a folded state when the satellite is launched. It is folded and pressed against the side edge of the satellite through the solar wing pressing and releasing device, and the solar blanket 505 is folded between the fixing rod 501 and the supporting rib assembly 502. After the satellite enters orbit, the solar wing pressing and releasing device is released, and first the fixing rod 501 is unfolded to a predetermined position through the root hinge 503, and then the supporting rib assembly 502, driven by the unfolding driving mechanism 504, drives the solar blanket 505 to gradually unfold around the central unfolding mechanism 504 to form a circular surface.

[0047] It should be noted that, for the technical solution provided in the embodiment of the present invention, each satellite platform is equipped with two foldable satellite solar wings 50, and the radius of the circumscribed circle of each foldable satellite solar wing 50 after unfolding is designed to be 1.2±0.2 meters, and the area of ​​solar cells that can be laid on a single wing is about 4.2±1.2 square meters. A triple-junction gallium arsenide solar cell with an efficiency of 32%±2% is used, and the laying efficiency is 80%±5%. The output power of a single wing is better than 950 watts, and the output power of a double wing is better than 1900 watts. In the specific implementation process, the number and area of ​​the solar wings can be determined according to actual conditions.

[0048] The folding optical payload camera 40 is composed of a main load-bearing plate, a primary mirror, a secondary mirror, and a light shield. The main load-bearing plate directly supports the flexible truss; the primary mirror, the secondary mirror, and the light shield are respectively connected to the main load-bearing plate through flexible trusses, which are folded during the launch phase and released and unfolded after entering orbit; when the satellite is launched, the main load-bearing plate of the folding optical payload camera 40 is fixed to the bottom plate of the satellite platform payload cabin, and the primary mirror, the secondary mirror, and the light shield are in a folded state and located inside the folding optical payload camera 40; after the satellite enters orbit, the flexible truss is unfolded and locked, and the primary mirror and the secondary mirror arrive at the predetermined position along with the unfolded flexible truss to form an optical system, and the light shield arrives at the predetermined position along with the unfolded flexible truss to form a stray light suppression system.

[0049] It should be noted that, for the technical solution provided in the embodiment of the present invention, the weight of the camera optical machine body is less than 60 kg, the imaging resolution is 0.3 m ± 0.05 m at an orbital altitude of 600 km, and the imaging width is 10 km ± 0.1 km. In the specific implementation process, different optical payload cameras can be configured according to the mission requirements.

[0050] The embodiment of the present invention adopts the overall compression release form, such as Figure 5For satellite stacking batch launching, the stacking type clamping release device 60 is composed of a clamping connection column 601, a locking column 602, and a clamping connection separation spring 603. The compression connection column 601 is installed on the side of the upper and lower side plates and the partition of the satellite main structure by screws. In the process of docking multiple satellites with the compression device, the multiple satellites are first aligned through the positioning grooves on the compression connection column 601, and then the locking column 602 is installed in the guide grooves of all the compression connection columns 601 of the multiple satellite assembly. The locking column 602 is connected to the launch vehicle adapter through a hinge, and then a pre-tightening force is applied to the top of the locking column 602 in the direction of the multiple satellite assembly to press the compression connection column 601 of each satellite, so as to realize the compression and fixed connection between the multiple satellite assembly and the launch vehicle; the compression connection separation spring 603 is set at the lower structural plate of each satellite main structure near the compression connection seat 601. After the multiple satellites are docked and compressed, the upper structural plate of the lower satellite and the lower structural plate of the upper satellite put the separation spring 603 in a compressed state to store elastic potential energy. After the satellite enters orbit, the pre-tightening force at the top of the locking column 602 is released, and it is unfolded 45±5° to ensure the safety of the separation of each satellite. The elastic potential energy stored in the compression connection separation springs 603 between the satellites is released and converted into kinetic energy, providing a relative separation speed for each satellite to eject the satellite. By setting the separation springs 603 between the satellites to different stiffnesses, it is ensured that the satellites are separated in an orderly and safe manner at different separation speeds.

[0051] It should be noted that, in the specific implementation process, the stacking type pressing and releasing device 60 can also adopt a point-type connection pressing and unlocking device 604 and a point-type connection separation spring 605, such as Figure 6 As shown, in the single satellite state, the upper flange of the point-type connection pressing and unlocking device 604 is installed to the four corner positions of the lower surface of the lower structure plate 20 of the satellite, and then the satellite with the point-type connection pressing and unlocking device 604 installed is installed to the upper surface of the upper structure plate 10 of the lower satellite through the lower flange of the point-type connection pressing and unlocking device 604, and the above steps are repeated in sequence to finally form a multi-satellite stacking launch assembly; the point-type connection separation spring 605 is installed at the adjacent position of the point-type connection pressing and unlocking device 604. After the satellite is launched into orbit, the point-type connection pressing and unlocking device 604 of the uppermost satellite is first powered and unlocked, and the uppermost satellite is ejected under the action of its own point-type connection separation spring 605 to achieve separation; then the point-type connection pressing and unlocking device 604 of the second upper satellite is powered and unlocked, and the second upper satellite is ejected under the action of its own point-type connection separation spring 605 to achieve separation; and so on, finally all satellites are separated in an orderly and safe manner in orbit. In the specific implementation process, the number of pressing and connecting columns or point-type connection pressing and unlocking mechanisms can be determined according to actual conditions.

[0052] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0053] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. All other embodiments obtained by ordinary technicians in this field without creative work based on the embodiments of the present invention are within the protection scope of the present invention.

[0054] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in this field.

Claims

1. A stacked optical remote sensing satellite platform, characterized in that include: A satellite main structure, two foldable satellite solar wings (50) and a stacking type compression release device (60), wherein: The satellite main structure comprises: an upper structural plate (10), a lower structural plate (20) and two partition plates (30), wherein: the upper structural plate (10) and the lower structural plate (20) have the same shape and are parallel in position, and each partition plate (30) vertically connects the opposite surfaces of the upper structural plate (10) and the lower structural plate (20) to form a three-dimensional space together; A foldable satellite solar wing (50) is installed on the satellite main structure through a solar wing compression and release device during the satellite launch phase, and provides energy for the satellite after being unfolded in orbit; The stacking type pressing and releasing device (60) is installed on the satellite main structure and is used to press the assembly formed by multiple satellites during stacking and launching, and to release the assembly formed by multiple satellites during on-orbit satellite-rocket separation.

2. A stacked optical remote sensing satellite platform according to claim 1, characterized in that: The top view projection of the satellite main structure configuration is the shape of the upper structure plate (10), which is a symmetrical polygon; The satellite main structure is an overall flat box-type structure, capable of carrying a foldable optical payload camera (40), and the height of the satellite main structure is the same as the height of the foldable optical payload camera (40) after being folded; a hole is opened in the center of the upper structure plate, and a part of the structure of the foldable optical payload camera (40) can extend from the opening of the upper structure plate (10); the lower structure plate is a complete structure plate, and the foldable optical payload camera (40) is installed on the inner surface of the lower structure plate.

3. A stacked optical remote sensing satellite platform according to claim 2, characterized in that: Before being deployed on orbit, the two foldable satellite solar wings (50) are respectively folded and pressed against the upper structural plate (10) or the lower structural plate (20) of the satellite main structure.

4. The stacked optical remote sensing satellite platform according to claim 1, characterized in that: The foldable satellite solar wing (50) is a circular deployable structure, comprising: a fixing rod (501), a support rib assembly (502), a root hinge (503), an unfolding drive mechanism (504), a solar blanket (505), and a solar cell sheet; specifically: The fixing rod (501) is connected to the satellite main structure through a hinge (503) at the root, and the other end is connected to the unfolding driving mechanism (504); the supporting rib assembly (502) includes a plurality of supporting ribs, one end of each supporting rib is connected to the unfolding driving mechanism (504), and the other end is suspended in the air; the solar blanket (505) is attached to the supporting ribs of the supporting rib assembly (502), and the solar cells are distributed on the solar blanket (505); In the unfolded state, the support rib assembly (502) is radially arranged with the unfolding drive mechanism (504) as the center, and the solar blanket (505) is spread on the support rib assembly (502). In the folded state, the support rib assembly (502) is parallel to the fixing rod (501), and the solar blanket (505) is folded according to the state of the support rib assembly (502).

5. The stacked optical remote sensing satellite platform according to claim 4, characterized in that: The foldable satellite solar wing (50) is in a folded state when the satellite is launched, and is folded and pressed against the edge of the satellite main structure by a solar wing pressing and releasing device; after the satellite enters orbit, the solar wing pressing and releasing device is released, and the fixing rod (501) moves to a predetermined position through a root hinge (503), and then the support rib assembly (502) is driven by an unfolding driving mechanism (504) to drive the solar blanket (505) to gradually unfold around the central unfolding mechanism (504) to form a circular surface.

6. The stacked optical remote sensing satellite platform according to claim 5, characterized in that: Each satellite platform is equipped with two foldable satellite solar wings (50), each foldable satellite solar wing (50) uses a triple-junction gallium arsenide solar cell sheet with an efficiency of 32%±2%, a sheet efficiency of 80%±5%, a single-wing output power better than 950 watts, and a double-wing output power better than 1900 watts.

7. The stacked optical remote sensing satellite platform according to claim 1, characterized in that: Each stacked compression release device (60) comprises a compression connection column (601), a locking column (602), and a compression connection separation spring (603); wherein: the compression connection column (601) is installed on the satellite main structure parallel to the vertical side of the partition (30); During the docking process between the multiple satellite platforms and the clamping device, the multiple satellite platforms are aligned through the positioning grooves on the clamping connection column (601), the locking column (602) is installed in the guide grooves of all the clamping connection columns (601) of the multiple satellite platform assembly, the bottommost locking column (602) is connected to the launch vehicle adapter through a hinge, and at the same time, a pre-tightening force is applied to the top locking column (602) in the direction of the multiple satellite platform assembly to press the clamping connection columns (601) of each satellite platform, thereby realizing a clamped and fixed connection between the multiple satellite platform assembly and the launch vehicle; A compression connection separation spring (603) is arranged adjacent to a compression connection seat (601) on the lower surface of a lower structural plate (20) of each satellite platform; after a plurality of satellites are docked and compressed, the upper structural plate (10) of the lower satellite platform and the lower structural plate (20) of the upper satellite platform put the separation spring (603) in a compressed state to store elastic potential energy; after the satellite enters orbit, the preload force at the top of the locking column (602) is released and unfolded at 45±5°, so that each satellite can be separated safely.

8. The stacked optical remote sensing satellite platform according to claim 1, characterized in that: The stacking type pressing and releasing device (60) adopts a point-type connection pressing and unlocking device (604) and a point-type connection separation spring (605), specifically: When the satellite platform is in a non-stacked state, the upper flange of the point-type connection, pressing and unlocking device (604) is installed at the four corners of the lower surface of the lower structural plate (20) of the satellite platform, and the satellite platform on which the point-type connection, pressing and unlocking device (604) has been installed is installed to the upper surface of the upper structural plate (10) of the lower satellite platform through the lower flange of the point-type connection, pressing and unlocking device (604), and the installation is repeated in sequence to form a multi-satellite stacking launch assembly; the point-type connection separation spring (605) is installed at an adjacent position of the point-type connection, pressing and unlocking device (604); After the satellite is launched into orbit, the point-type connection pressing and unlocking devices (604) from top to bottom are powered and unlocked in sequence, and the corresponding satellite platforms are ejected in sequence under the action of their own point-type connection separation springs (605) to achieve separation.

9. The stacked optical remote sensing satellite platform according to claim 1, characterized in that: The three-dimensional space formed by the upper structural plate (10), the lower structural plate (20) and the two partition plates (30) in the satellite main structure can also be loaded with electronic and mechanical equipment including power supply and distribution, comprehensive data management, communication and attitude control functions.

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