A flat-panel SAR satellite with a standardized satellite platform

Abstract

The present invention provides a flat-plate SAR satellite with a standardized satellite platform, including a satellite platform, a solar array and a phased array antenna. In the launch state, the solar array and the phased array antenna are folded into a structure with the same size as the satellite platform. In the on-orbit state, the phased array antenna is unfolded and parallel to the unfolded solar array. The present invention adopts a flat-plate configuration, the internal space of the platform is compact, the outer envelope shape of the whole satellite is regular, and the size distribution of each dimension is reasonable, which is convenient for one-shot multi-satellite layout, and can adapt to the internal space of most carrier fairings on the market to achieve rapid constellation networking; in the later stage, the satellite platform does not need to be replaced for SAR payloads of different sizes, thereby shortening the development cycle and reducing the development cost; the mechanical interface of the present invention is simple, the size of the satellite platform is minimized to be affected by the load change, and the AIT cycle of the whole satellite is effectively shortened; the thruster of the present invention is installed on the satellite platform through an adjustable bracket, and it is convenient to meet the thruster installation requirements through rough and fine position adjustment in the later stage.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, and in particular to a flat-panel SAR satellite with a standardized satellite platform. Background Art

[0002] The phased array antennas carried by SAR satellites are generally thin plate-shaped. In order to occupy a smaller envelope space of the fairing during launch, the phased array antennas usually divide the entire antenna into multiple antenna sub-arrays along the azimuth direction. They are in a folded state during launch and unfolded to form a coplanar shape after being released in orbit.

[0003] Early SAR satellites were large in size and had high gravity. They were mostly launched in a single-satellite / double-satellite launch mode. The fairing allocated more space to the satellite. At this time, the middle subarray of the SAR satellite's phased array antenna was directly fixed to the +Z (ground) cabin of the satellite, and the two side subarrays were respectively installed on the ±X cabin of the satellite through the unfolding hinge and the clamping release mechanism. After the on-orbit release, the three antenna subarrays unfolded to form a coplanar structure, such as Figure 1a , 1b As shown, this configuration will result in a higher height of the satellite platform and a larger envelope size when folded up.

[0004] At present, some SAR satellite phased array antennas are divided into three antenna sub-arrays. The middle sub-array is longer and the two side sub-arrays are shorter. The three antenna sub-arrays are gathered on the same side, but the two side sub-arrays are gathered on the middle sub-array. Figure 2a , 2b As shown. When deployed on orbit, the two side sub-arrays are deployed around the deployment mechanism. This configuration will result in a larger length of the satellite platform, and a larger envelope size when folded up, which is more critical to the size of the carrier fairing.

[0005] The above two SAR satellite configurations have low requirements for the complexity of the phased array antenna deployment mechanism, but will lead to problems with the height or length of the satellite platform. The folding and compacting method on both sides of the sub-array will have interfaces with the three cabin panels of the satellite platform, which will increase the complexity of the final assembly during the AIT stage; the folding and compacting method of the sub-arrays on the same side, the different sizes of the three sub-arrays increase the complexity of structural manufacturing, and the size of the satellite platform is longer in the folded state, resulting in the non-compact space of the single machine in the platform cabin and a large remaining space.

[0006] At present, satellites are developing towards lightweight and low-cost. Aerospace often adopts multiple satellites per launch or carpooling launch, which can not only quickly complete the networking and constellation construction, but also effectively reduce the cost of satellite launch. The above two types of SAR satellites have at least one dimension of the envelope that is larger, and the internal space of the whole satellite is not compact enough, which is not convenient for the layout of multiple satellites and the size and space of the carrier fairing are more picky.

[0007] Therefore, there is a need for a SAR satellite that is applicable to a multi-star configuration. Summary of the invention

[0008] The present invention is to solve the problem of how to facilitate the layout of multiple satellites and the size and space suitable for the carrier fairing, and provides a flat-plate SAR satellite with a standardized satellite platform, including a satellite platform, a solar array and a phased array antenna. In the launch state, the solar array and the phased array antenna are folded into a structure with the same size as the satellite platform, and in the on-orbit state, the phased array antenna is unfolded and parallel to the unfolded solar array. The present invention adopts a flat-plate configuration, the internal space of the platform is compact, the outer envelope shape of the whole satellite is regular, and the size distribution of each dimension is reasonable, which is convenient for the layout of multiple satellites with one arrow, and can adapt to the internal space of most carrier fairings on the market, and realize the rapid networking of constellations; in the later stage, the satellite platform does not need to be replaced for SAR payloads of different sizes, thereby shortening the development cycle and reducing the development cost; the mechanical interface of the present invention is simple, the size of the satellite platform is minimized by the load change, and the AIT cycle of the whole satellite is effectively shortened; the thruster of the present invention is installed on the satellite platform through an adjustable bracket, and it is convenient to meet the thruster installation requirements through rough and fine position adjustment in the later stage.

[0009] The present invention provides a flat-panel SAR satellite with a standardized satellite platform, comprising a satellite platform, a solar cell array folded and pressed on the sky side of the satellite platform during launch, and a phased array antenna folded and pressed on the ground side of the satellite platform during launch. In the launch state, the solar cell array and the phased array antenna are folded into a structure with the same size as the satellite platform. In the on-orbit state, the phased array antenna is unfolded and parallel to the unfolded solar cell array.

[0010] The solar cell array comprises a first solar cell sub-array connected to the sky-facing surface of the star platform, a second solar cell sub-array connected to one end of the first solar cell sub-array, and a third solar cell sub-array connected to the other end of the first solar cell sub-array. The first solar cell sub-array, the second solar cell sub-array and the third solar cell sub-array are all plate-shaped and have the same size.

[0011] In the launching state, the second solar cell subarray and the third solar cell subarray are folded together at the same side and pressed against the first solar cell subarray, and the third solar cell subarray is located above the second solar cell subarray; in the on-orbit state, the third solar cell subarray and the second solar cell subarray are respectively unfolded to both sides around the first solar cell subarray, and after unfolding, the first solar cell subarray, the second solar cell subarray and the third solar cell subarray form a coplanar surface;

[0012] The phased array antenna includes a first phased array antenna connected to the ground side surface of the satellite platform, and a second phased array antenna and a third phased array antenna respectively connected to two ends of the first phased array antenna, and the first phased array antenna, the second phased array antenna and the third phased array antenna are all plate-shaped antennas and have the same size;

[0013] In the transmitting state, the second phased array antenna and the third phased array antenna are folded high and low on the same side and pressed tightly on the first solar cell subarray, and the third phased array antenna is located above the second phased array antenna; in the on-orbit state, the third phased array antenna and the second phased array antenna are respectively unfolded to both sides around the first phased array antenna, and after unfolding, the first phased array antenna, the second phased array antenna and the third phased array antenna form a coplanar surface;

[0014] The flat-panel SAR satellite with a standardized satellite platform described in the present invention, as a preferred embodiment, the satellite platform includes a satellite structure, a satellite-rocket adapter connected to the four corners of the satellite structure respectively, and a subsystem component connected inside and outside the satellite structure;

[0015] The star structure is a box-type structure consisting of aluminum-skinned honeycomb sandwich panels;

[0016] The satellite structure includes a +X cabin board and a -X cabin board that are arranged oppositely, a +Y cabin board and a -Y cabin board that are arranged oppositely, a +Z cabin board and a -Z cabin board that are arranged oppositely, and a partition board that is connected between the +Y cabin board and the -Y cabin board and is parallel to the +X cabin board and the -X cabin board, a first solar cell sub-array is connected to the -Z cabin board, and a first phased array antenna is connected to the +Z cabin board;

[0017] The +X cabin board, -X cabin board, +Y cabin board, -Y cabin board, -Z cabin board and bulkhead are first assembled and then assembled with the +Z cabin board.

[0018] The flat-panel SAR satellite with a standardized satellite platform described in the present invention, as a preferred embodiment, the subsystem components include a data transmission antenna connected outside the satellite structure cabin, a ground telemetry and remote control antenna, a main star sensor, a GNSS antenna, a spare star sensor, a sky telemetry and remote control antenna, an electric thruster, a magnetic torque device Z and a battery pack connected inside the satellite structure cabin, integrated electronics, a high-performance computer, an electric propulsion controller, a momentum wheel, a momentum wheel S, a momentum wheel X, an electric propulsion tank, a load controller, a magnetic torque Y, a momentum wheel Z, a magnetic torque X, a data transmission transmitter, a power supply controller, a fiber optic gyroscope, and a magnetometer;

[0019] The number of the magnetic torquers Z and the number of the magnetometers are both two.

[0020] The flat-panel SAR satellite with a standardized satellite platform described in the present invention is preferably configured such that the data transmission antenna, the ground telemetry and remote control antenna, the primary star sensor, the Taimin and the GNSS antenna are located on the same X-direction cabin panel or the Y-direction cabin panel, the backup star sensor, the sky telemetry and remote control antenna, the electric thruster and the magnetic torquer Z are located on the cabin panel on the opposite side, and the thrust line of the electric thruster is close to the center of mass of the flat-panel SAR satellite and does not block the plume;

[0021] The connection points of the second solar cell subarray, the third solar cell subarray and the first solar cell subarray, and the connection points of the second phased array antenna, the third phased array antenna and the first phased array antenna are located on the cabin plate adjacent to the subsystem component.

[0022] The flat-panel SAR satellite with a standardized satellite platform described in the present invention, as a preferred embodiment, the electric thruster includes a mounting bracket, an adjustment gasket connecting the mounting bracket to the outside of the satellite structure cabin plate by screws, and a thrust chamber connected to the mounting bracket;

[0023] The fixing positions of the mounting bracket and the adjusting gasket are adjustable, while the fixing positions of the mounting bracket and the thrust chamber remain unchanged. The mounting bracket can be adjusted to install the thrust chamber with multiple degrees of freedom by adjusting the gasket without changing the mounting interface of the satellite structure to meet the attitude control accuracy requirements of the flat-panel SAR satellite.

[0024] The flat-panel SAR satellite with a standardized satellite platform described in the present invention, as a preferred embodiment, the mounting bracket includes a mounting bracket body, a mounting interface connected to the mounting bracket body, and an adjustment gasket interface connected to the edge of the mounting bracket body;

[0025] The mounting bracket body is a plate-like structure, and the adjustment gasket interface is a stepped circular opening;

[0026] The adjusting gasket comprises a first disc structure and a second disc structure connected vertically and coaxially, a straight slot connected through the centers of the first disc structure and the second disc structure, and circular holes symmetrically connected to the first disc structure on both sides of the straight slot; the diameter of the first disc structure is greater than the diameter of the second disc structure, and the straight slot is an oblong opening;

[0027] The adjusting gasket can be rotated 360 degrees in the adjusting gasket interface to drive the straight slot to rotate, and the fixing position of the mounting bracket on the star structure mounting cabin plate can be adjusted by rotating the adjusting gasket left and right, up and down, and forward and reverse directions.

[0028] The flat-panel SAR satellite with a standardized satellite platform described in the present invention, as a preferred embodiment, the mounting bracket further includes a weight reduction port;

[0029] There are four mounting interfaces, which are symmetrically distributed. There are four adjustment gasket interfaces and four adjustment gaskets. The adjustment gasket interfaces are located at the four corners of the mounting bracket body, and the mounting interfaces are distributed between the adjustment gasket interfaces.

[0030] The flat-panel SAR satellite with a standardized satellite platform described in the present invention is preferably configured such that the number of the solar array and the phased array antenna sub-array is greater than or equal to 3, and the sub-arrays are respectively gathered high and low on the same side and pressed tightly against the sky side and the ground side of the satellite platform.

[0031] The flat-panel SAR satellite with a standardized satellite platform described in the present invention, as a preferred embodiment, the method for assembling the flat-panel SAR satellite comprises the following steps:

[0032] S1. Assemble the +X cabin board, -X cabin board, +Y cabin board, -Y cabin board, -Z cabin board and partition board of the satellite platform into the satellite structure components by screws;

[0033] S2. Install the subsystem single-machine components of the satellite platform onto the satellite structure components, with uniform inertia distribution, leaving space for cable laying operations and meeting the technical requirements of each single-machine component for installation;

[0034] S3, installing and debugging the +Z cabin board and the phased array antenna of the satellite platform to obtain the phased array antenna component;

[0035] S4, docking the satellite structure components and the phased array antenna components;

[0036] S5. Carry out final assembly, testing and experiment of flat-panel SAR satellite. Once qualified, a flat-panel SAR satellite with a standardized satellite platform is assembled.

[0037] The flat-panel SAR satellite with a standardized satellite platform described in the present invention is preferably configured such that in step S3, when the size of the phased array antenna needs to be changed, only the size of the +Z cabin needs to be adjusted;

[0038] In step S5, when debugging the electric thruster of the satellite platform, the coordinates of the center of mass position of the flat-panel SAR satellite are measured by the quality test platform, and then the coordinates of the thrust axis of the thrust chamber on the installation plane are measured to calculate the installation error of the thrust chamber;

[0039] When the thrust chamber installation error is greater than the threshold, the position of the thrust chamber is adjusted. The adjustment method is: by comparing and calculating with the thrust chamber installation requirements proposed by the attitude control subsystem of the satellite platform, the distance and orientation that the thrust chamber needs to move relative to the current installation state are obtained; use a marker to mark the position of the mounting bracket that needs to be adjusted on the mounting cabin plate of the satellite platform, loosen the mounting screws on the 4 adjustment gaskets and rotate the adjustment angle until the mounting bracket is adjusted to the marked position, and then tighten the 4 mounting screws, and the position adjustment of the thrust chamber is completed.

[0040] The present invention has the following advantages:

[0041] (1) The SAR satellite of the present invention adopts a flat-plate configuration, the internal space of the platform is compact, the outer envelope of the entire satellite has a regular shape, and the size distribution of each dimension is reasonable, which is convenient for the layout of multiple satellites with one rocket, can adapt to the internal space of most carrier fairings on the market, and can realize rapid constellation networking;

[0042] (2) The SAR satellite of the present invention adopts a standardized satellite platform, and the payload is a flat-panel radar phased array antenna payload (SAR payload). In the later stage, it is not necessary to replace the satellite platform for SAR payloads of different sizes, thereby shortening the development cycle and reducing the development cost;

[0043] (3) In order to adapt to the changes in the size and weight of different SAR payloads, the standardized satellite platform of the present invention uses a cabin panel to install the SAR payload, and the mechanical interface is simple. Therefore, the size of the satellite platform is minimized by the impact of the load change. In addition, the installation and adjustment of the cabin panel and the SAR payload can also be carried out on the payload side, effectively shortening the AIT (assembly, test, and experiment) cycle of the entire satellite.

[0044] (4) The thruster of the attitude control equipment installed on the SAR satellite platform of the present invention has high requirements for the installation position. The thrust axis is required to pass through the satellite's center of mass. In order to adapt to the changes in the satellite's center of mass caused by different SAR loads, the thruster is installed on the satellite platform through an adjustable bracket, which makes it convenient to meet the thruster installation requirements through rough and fine adjustments of the position in the later stage. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1a It is a schematic diagram of the folded state of the existing satellite configuration 1;

[0046] Figure 1b It is a schematic diagram of the unfolded state of the existing satellite configuration 1;

[0047] Figure 2a It is a schematic diagram of the folded state of the existing satellite configuration 2;

[0048] Figure 2b It is a schematic diagram of the unfolded state of the existing satellite configuration 2;

[0049] Figure 3 A schematic diagram of a flat-panel SAR satellite with a standardized satellite platform in a folded state;

[0050] Figure 4 A schematic diagram of the unfolded state of a flat-panel SAR satellite with a standardized satellite platform;

[0051] Figure 5 The figure is a schematic diagram of the structure of a flat-panel SAR satellite with a standardized satellite platform;

[0052] Figure 6 Another side view of the structure of a flat-panel SAR satellite with a standardized satellite platform;

[0053] Figure 7 This is an exploded view of the structure cabin of a flat-panel SAR satellite with a standardized satellite platform;

[0054] Figure 8A schematic diagram of the installation locations of components of a flat-panel SAR satellite subsystem with a standardized satellite platform;

[0055] Fig. 9 This is a state diagram of a flat-panel SAR satellite phased array antenna with a standardized satellite platform when its size changes;

[0056] Fig.10 It is a schematic diagram of the installation status of a flat-plate SAR satellite electric thruster with a standardized satellite platform;

[0057] Fig.11 A schematic diagram of a flat-plate SAR satellite electric thruster mounting bracket structure with a standardized satellite platform;

[0058] Fig.12 It is a structural diagram of a flat-plate SAR satellite electric thruster adjustment gasket with a standardized satellite platform;

[0059] Fig.13 The cross-sectional view of the adjustment gasket interface of a flat-plate SAR satellite electric thruster with a standardized satellite platform;

[0060] Fig.14 It is a cross-sectional view of the gasket interface of a flat-plate SAR satellite electric thruster assembly state adjustment with a standardized satellite platform;

[0061] Fig.15 A schematic diagram of the adjustment state of a flat-panel SAR satellite electric thruster with a standardized satellite platform;

[0062] Fig.16 The present invention is a flow chart of a method for assembling a flat-panel SAR satellite having a standardized satellite platform.

[0063] Reference numerals:

[0064] 1. Satellite platform; 11. Satellite structure; 111. +X cabin board; 112. -X cabin board; 113. +Y cabin board; 114. -Y cabin board; 115. +Z cabin board; 116. -Z cabin board; 12. Star-rocket adapter; 13. Subsystem components; 131. Data transmission antenna; 132. Ground telemetry and remote control antenna; 133. Main satellite sensor; 134. Taimin; 135. GNSS antenna; 1 36. Standby star sensor; 137. Sky telemetry remote control antenna; 138. Electric thruster; 1381. Mounting bracket; 13811. Mounting bracket body; 13812. Mounting interface; 13813. Adjustment gasket interface; 13814. Weight reduction port; 1382. Adjustment gasket; 13821. First disc structure; 13822. Second disc structure; 13823. Straight slot; 1382 4. Circular hole; 1383. Thrust chamber; 139. Magnetic torquer Z; 1310. Battery pack; 1311. Integrated electronics; 1312. High performance computer; 1313. Electric propulsion controller; 1314. Momentum wheel; 1315. Momentum wheel S; 1316. Momentum wheel X; 1317. Electric propulsion tank; 1318. Load controller; 1319. Magnetic torque Y; 1320. Momentum wheel Z; 1321. Magnetic torque X; 1322. Digital transmitter; 1323. Power controller; 1324. Fiber optic gyroscope; 1325. Magnetometer; 2. Solar cell array; 21. First solar cell subarray; 22. Second solar cell subarray; 23. Third solar cell subarray; 3. Phased array antenna; 31. First phased array antenna; 32. Second phased array antenna; 33. Third phased array antenna. DETAILED DESCRIPTION

[0065] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0066] Example 1

[0067] As shown in FIGS. 1 to 16 , a flat-panel SAR satellite with a standardized satellite platform includes a satellite platform 1, a solar array 2 that is folded and pressed on the sky side of the satellite platform 1 during launch, and a phased array antenna 3 that is folded and pressed on the ground side of the satellite platform 1 during launch. In the launch state, the solar array 2 and the phased array antenna 3 are folded into a structure with the same size as the satellite platform 1. In the on-orbit state, the phased array antenna 3 is unfolded and parallel to the unfolded solar array 2.

[0068] The solar cell array 2 includes a first solar cell sub-array 21 connected to the sky-side surface of the star platform 1, a second solar cell sub-array 22 connected to one end of the first solar cell sub-array 21, and a third solar cell sub-array 23 connected to the other end of the first solar cell sub-array 21. The first solar cell sub-array 21, the second solar cell sub-array 22, and the third solar cell sub-array 23 are all plate-shaped and have the same size.

[0069] In the launching state, the second solar cell subarray 22 and the third solar cell subarray 23 are folded together at the same side and pressed against the first solar cell subarray 21, and the third solar cell subarray 23 is located above the second solar cell subarray 22; in the on-orbit state, the third solar cell subarray 23 and the second solar cell subarray 22 are respectively unfolded to both sides around the first solar cell subarray 21, and after unfolding, the first solar cell subarray 21, the second solar cell subarray 22 and the third solar cell subarray 23 form a coplanar surface;

[0070] The phased array antenna 3 includes a first phased array antenna 31 connected to the ground side surface of the satellite platform 1, and a second phased array antenna 32 and a third phased array antenna 33 respectively connected to both ends of the first phased array antenna 31. The first phased array antenna 31, the second phased array antenna 32 and the third phased array antenna 33 are all plate-shaped antennas and have the same size.

[0071] In the transmitting state, the second phased array antenna 32 and the third phased array antenna 33 are folded and pressed against the first solar cell subarray 21 at the same side, and the third phased array antenna 33 is located above the second phased array antenna 32; in the on-orbit state, the third phased array antenna 33 and the second phased array antenna 32 are respectively unfolded to both sides around the first phased array antenna 31, and after unfolding, the first phased array antenna 31, the second phased array antenna 32 and the third phased array antenna 33 form a coplanar surface;

[0072] The satellite platform 1 includes a satellite structure 11, a satellite-rocket adapter 12 connected to the four corners of the satellite structure 11, and a subsystem component 13 connected inside and outside the satellite structure 11;

[0073] The star structure 11 is a plate box structure composed of aluminum skin honeycomb sandwich panels;

[0074] The satellite structure 11 includes a +X cabin board 111 and a -X cabin board 112 that are arranged oppositely, a +Y cabin board 113 and a -Y cabin board 114 that are arranged oppositely, a +Z cabin board 115 and a -Z cabin board 116 that are arranged oppositely, and a partition board 117 that is connected between the +Y cabin board 113 and the -Y cabin board 114 and is parallel to the +X cabin board 111 and the -X cabin board 112, the first solar cell sub-array 21 is connected to the -Z cabin board 116, and the first phased array antenna 31 is connected to the +Z cabin board 115;

[0075] The +X cabin board 111, -X cabin board 112, +Y cabin board 113, -Y cabin board 114, -Z cabin board 116 and bulkhead 117 are first assembled and then assembled with the +Z cabin board 115;

[0076] The subsystem assembly 13 includes a data transmission antenna 131 connected to the outside of the cabin of the satellite structure 11, a ground telemetry and remote control antenna 132, a main satellite sensor 133, a Taimin 134, a GNSS antenna 135, a spare satellite sensor 136, a sky telemetry and remote control antenna 137, an electric thruster 138, a magnetic torque device Z139, and a battery pack 1310 connected to the cabin of the satellite structure 11, an integrated electronics 1311, a high-performance computer 1312, an electric propulsion controller 1313, a momentum wheel 1314, a momentum wheel S1315, a momentum wheel X1316, an electric propulsion tank 1317, a load controller 1318, a magnetic torque Y1319, a momentum wheel Z1320, a magnetic torque X1321, a data transmission transmitter 1322, a power supply controller 1323, a fiber optic gyroscope 1324, and a magnetometer 1325;

[0077] There are two magnetic torquers Z139 and two magnetometers 1325;

[0078] The data transmission antenna 131, the ground telemetry and remote control antenna 132, the main satellite sensor 133, the Taimin 134 and the GNSS antenna 135 are located on the same X-direction cabin panel or the Y-direction cabin panel, the standby satellite sensor 136, the sky telemetry and remote control antenna 137, the electric thruster 138 and the magnetic torquer Z139 are located on the cabin panel on the opposite side, and the thrust line of the electric thruster 138 is close to the mass center of the flat-panel SAR satellite and does not block the plume;

[0079] The connection between the second solar cell subarray 22, the third solar cell subarray 23 and the first solar cell subarray 21, and the connection between the second phased array antenna 32, the third phased array antenna 33 and the first phased array antenna 31 are located on the deck adjacent to the subsystem component 13;

[0080] The electric thruster 138 includes a mounting bracket 1381, an adjustment gasket 1382 that connects the mounting bracket 1381 to the outside of the cabin plate of the satellite structure 11 through screws, and a thrust chamber 1383 connected to the mounting bracket 1381;

[0081] The fixing positions of the mounting bracket 1381 and the adjusting gasket 1382 are adjustable, and the fixing positions of the mounting bracket 1381 and the thrust chamber 1383 remain unchanged. The mounting bracket 1381 can be adjusted to install the thrust chamber 1383 with multiple degrees of freedom by adjusting the gasket 1382 without changing the mounting interface of the satellite structure 11 to meet the attitude control accuracy requirements of the flat-panel SAR satellite.

[0082] The mounting bracket 1381 includes a mounting bracket body 13811 , a mounting interface 13812 connected to the mounting bracket body 13811 , and an adjustment gasket interface 13813 connected to the edge of the mounting bracket body 13811 ;

[0083] The mounting bracket body 13811 is a plate-like structure, and the adjustment gasket interface 13813 is a stepped circular opening;

[0084] The adjusting gasket 1382 includes a first disc structure 13821 and a second disc structure 13822 which are vertically and coaxially connected, a straight slot 13823 which is connected through the centers of the first disc structure 13821 and the second disc structure 13822, and circular holes 13824 which are symmetrically connected on the first disc structure 13821 on both sides of the straight slot 13823; the diameter of the first disc structure 13821 is larger than the diameter of the second disc structure 13822, and the straight slot 13823 is an oblong opening;

[0085] The adjusting gasket 1382 can rotate 360 ​​degrees in the adjusting gasket interface 13813 to drive the straight slot 13823 to rotate, and the fixing position of the mounting bracket 1381 on the mounting cabin plate of the star structure 11 can be adjusted by rotating the adjusting gasket 1382 left and right, up and down, and forward and reverse;

[0086] The mounting bracket 1381 also includes a weight-reducing opening 13814;

[0087] The number of mounting interfaces 13812 is 4 and they are symmetrically distributed. The number of adjustment gasket interfaces 13813 and adjustment gaskets 1382 are both 4. The adjustment gasket interfaces 13813 are located at the four corners of the mounting bracket body 13811. The mounting interfaces 13812 are distributed between the adjustment gasket interfaces 13813.

[0088] The number of the solar cell array 2 and the phased array antenna 3 sub-arrays is greater than or equal to 3, and they are respectively gathered high and low on the same side and pressed tightly on the sky side and the ground side of the satellite platform 1;

[0089] The assembly method of the flat-panel SAR satellite includes the following steps:

[0090] S1. Assemble the +X cabin board 111, -X cabin board 112, +Y cabin board 113, -Y cabin board 114, -Z cabin board 116 and partition board 117 of the star platform 1 into the star structure components by screws;

[0091] S2. Install the subsystem single-machine components of the satellite platform 1 onto the satellite structure components, with uniform inertia distribution, leaving space for cable laying operations and meeting the technical requirements of each single-machine component for installation;

[0092] S3. Install and debug the +Z cabin board 115 and the phased array antenna 3 of the satellite platform 1 to obtain the phased array antenna component; when the size of the phased array antenna 3 needs to be changed, it is only necessary to adjust the size of the +Z cabin board 115;

[0093] S4, docking the satellite structure components and the phased array antenna components;

[0094] S5. Carry out the final assembly, testing and experiment of the flat-panel SAR satellite. After passing the test, a flat-panel SAR satellite with a standardized satellite platform is assembled;

[0095] In step S5, when debugging the electric thruster 138 of the satellite platform 1, the coordinates of the center of mass position of the flat-panel SAR satellite are measured by the mass testing platform, and then the coordinates of the thrust axis of the thrust chamber 138 on the installation plane are measured, and the installation error of the thrust chamber 138 is calculated;

[0096] When the thrust chamber installation error is greater than the threshold, the position of the thrust chamber 138 is adjusted. The adjustment method is: by comparing and calculating with the thrust chamber 138 installation requirements proposed by the attitude control subsystem of the satellite platform 1, the distance and orientation that the thrust chamber 138 needs to move relative to the current installation state are obtained; use a marker to mark the position of the mounting bracket 1381 that needs to be adjusted on the mounting cabin plate of the satellite platform 1, loosen the mounting screws on the four adjustment gaskets 1382 and rotate the adjustment angle until the mounting bracket 1381 is adjusted to the marked position, and then tighten the four mounting screws, and the position adjustment of the thrust chamber 138 is completed.

[0097] Figure 3 , Figure 4 The figure shows the configuration and composition of a flat-panel SAR satellite. Figure 3 The whole star is in a folded state. Figure 4 The satellite is in the state of being deployed in orbit. The satellite mainly consists of three parts: the satellite platform 1, the solar array 2 and the phased array antenna 3. The solar cell array 2 is folded and pressed on the sky side (-Z side of the satellite coordinate system) of the satellite platform 1, and the phased array antenna 3 is folded and pressed on the ground side (+Z side of the satellite coordinate system) of the satellite platform 1; the solar cell array 2 and the phased array antenna 3 are both composed of three identical sub-arrays, and in the launch state, the two unfolded sub-arrays are folded and pressed on the body-mounted sub-array at the same side, and in the on-orbit state, the two unfolded sub-arrays are unfolded around the two sides of the body-mounted sub-array, and the three sub-array panels form a coplanar surface; because the solar cell array 2 and the phased array antenna 3 are respectively installed with a certain cabin plate of the satellite platform 1, the configuration and size of the satellite platform 1 are less restricted, and the assembly and docking process is simple, and the size changes of the solar cell array 2 and the phased array antenna 3 in the later stage do not affect the satellite platform 1; this configuration of the satellite has the advantages of thin overall thickness, uniform length, width and height distribution, regular outer envelope shape, and is convenient for the layout of multiple satellites in one rocket, and is suitable for the internal space of most carrier fairings on the market.

[0098] Figures 5 to 8 The satellite platform 1 is described in detail. It mainly includes a satellite structure 11, a satellite-rocket adapter 12 and each subsystem unit configuration. Each subsystem unit and equipment are installed inside and outside the satellite structure 11, and some extravehicular equipment is installed using brackets. The satellite-rocket adapter 12 is installed to the four corners of the satellite structure 11 through the adapter bracket.

[0099] The satellite structure 11 is a plate-box structure composed of aluminum skin honeycomb sandwich panels, which contains a total of 7 structural panels to form the main load-bearing structure of the entire satellite. The outer dimensions of the satellite structure 11 are 1000mm*960mm*220mm. According to the definition rules of the mechanical coordinate system of the entire satellite, it includes: +X cabin plate 111, -X cabin plate 112, +Y cabin plate 113, -Y cabin plate 114, +Z cabin plate 115, -Z cabin plate 116, and partition plate 117. Except for the +Z cabin plate 115, the remaining 6 plates are assembled as a whole by screws. After the +Z cabin plate 115 and the phased array antenna 3 are installed and debugged, they are docked with the satellite structure. The installation and debugging of the +Z cabin plate 115 and the phased array antenna 3 can also be carried out on the payload side, which can shorten the AIT (assembly, testing, and experiment) cycle of the entire satellite.

[0100] Each subsystem unit and equipment is installed inside and outside the satellite structure 11. The extravehicular equipment mainly includes: a data transmission antenna 131, a ground telemetry and remote control antenna 132, a main star sensor 133, a Taimin 134, a GNSS antenna 135, a spare star sensor 136, a sky telemetry and remote control antenna 137, an electric thruster 138, and two magnetic torquers Z 139; the intravehicular equipment mainly includes: a battery pack 1310, an integrated electronics 1311, a high-performance computer 1312, an electric propulsion controller 1313, a momentum wheel Y 1314, a momentum wheel S 1315, a momentum wheel X 1316, an electric propulsion tank 1317, a load controller 1318, a magnetic torque Y 1319, a momentum wheel Z 1320, a magnetic torque X 1321, a data transmission transmitter 1322, a power supply controller 1323, a fiber optic gyroscope 1324, and two magnetometers 1325. The equipment layout has the following characteristics: the platform equipment layout is compact; the platform inertia is as evenly distributed as possible (I xx , I yy , I zz leave enough space for cable laying and meet the technical requirements of each single machine for installation, etc.

[0101] like Fig. 9 As shown: since the +Z cabin plate 115 is installed with the phased array antenna 3, when the size of the phased array antenna 3 is subsequently changed, it is only necessary to change the size of the +Z cabin plate 115, and other configuration layouts remain unchanged.

[0102] like Figures 10 to 15As shown, the electric thruster 138 mainly includes a mounting bracket 1381 , an adjustment gasket 1382 , and a thrust chamber 1383 .

[0103] Adjust the shims as Fig.12 As shown, the adjustment gasket 1382 is a right T-shaped circular configuration, and there are two circular hole features 13824 on the adjustment gasket, which is convenient for using external tooling to rotate and adjust the gasket through the circular holes. A straight slot feature 13823 is left on the adjustment gasket, which allows the connecting screw to move within a small range in the straight slot. After adjusting the screw position, tighten the screw to fix the thrust chamber. The total thickness of the T-shaped circular configuration is 4.7mm, the diameter of the circular hole feature 13824 is φ2mm, and the distance between the two holes of the straight slot feature 13823 is 6mm, and 6mm is the adjustable range.

[0104] like Fig.11 As shown, the mounting bracket 1381 has four mounting interfaces 13813 for the thrust chamber 1383. After the thrust chamber 1383 is mounted on the mounting bracket 1381, there is no need to adjust the relative position. The mounting bracket 1381 is connected to the mounting cabin through four adjustment gasket interfaces 1382. Each adjustment gasket is fixed with an M5 screw. The mounting bracket 1381 has a weight reduction opening 13814 to reduce the weight of the bracket. The mounting bracket is symmetrical in configuration, with an outer dimension of 115mm×115mm×5mm, and the mounting interface 13813 is a threaded hole feature.

[0105] like Fig.13 and Fig.14 As shown, the adjustment gasket interface 13812 is a right T-shaped circular configuration, which cooperates with the adjustment gasket 1382. The adjustment gasket 1382 can rotate 360 ​​degrees in the adjustment gasket interface 13812, thereby driving the straight slot feature 13823 on the adjustment gasket 1382 to rotate, so that the fixed position of the mounting bracket 1381 on the mounting cabin plate can be adjusted.

[0106] like Fig.15 As shown, by adjusting the rotation angle of the adjustment gasket interface 13812 of the four adjustment gaskets 1382 on the mounting bracket 1381, the fixed position of the thrust chamber 1383 on the mounting cabin plate on the mounting bracket 1381 is adjusted. This method can adjust the thrust chamber to the left and right, up and down, and forward and reverse rotations within the plane of the mounting cabin plate 1.

[0107] The specific implementation method of the electric thruster 138 is:

[0108] Installation status is Fig.10As shown, when the satellite is assembled, the coordinates of the satellite center of mass are measured by the quality test platform, and the coordinates of the thrust axis of the thrust chamber 1383 on the installation plane are measured by the precision measuring instrument, so as to obtain the installation error of the thrust chamber 1383. If the installation error is large, the distance and orientation that the thrust chamber needs to move relative to the current installation state are further calculated by comparing with the thrust chamber installation requirements proposed by the attitude control subsystem. Use a marker to mark the position that the mounting bracket 1381 needs to be adjusted, loosen the mounting screws on the four adjustment gaskets 1382, rotate the four adjustment gaskets 1382 to the appropriate angles, until the mounting bracket 1381 is adjusted to the marked position, and then restore the tightening state of the four mounting screws to complete the thrust chamber position adjustment work.

[0109] Fig.16 The present invention provides an assembly method for a flat-panel SAR satellite, which has high adaptability.

[0110] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A flat-panel SAR satellite with a standardized satellite platform, characterized in that: It comprises a satellite platform (1), a solar cell array (2) which is folded and pressed on the sky side of the satellite platform (1) during launch, and a phased array antenna (3) which is folded and pressed on the ground side of the satellite platform (1) during launch; in the launch state, the solar cell array (2) and the phased array antenna (3) are folded into a structure with the same size as the satellite platform (1); in the on-orbit state, the phased array antenna (3) is unfolded and parallel to the unfolded solar cell array (2); The satellite platform (1) comprises a satellite structure (11), a satellite-rocket adapter (12) respectively connected to the four corners of the satellite structure (11), and a subsystem component (13) connected inside and outside the satellite structure (11), wherein the subsystem component (13) comprises an electric thruster (138) connected outside the cabin of the satellite structure (11); The solar cell array (2) comprises a first solar cell sub-array (21) connected to the sky-facing surface of the star platform (1), a second solar cell sub-array (22) connected to one end of the first solar cell sub-array (21), and a third solar cell sub-array (23) connected to the other end of the first solar cell sub-array (21); the first solar cell sub-array (21), the second solar cell sub-array (22), and the third solar cell sub-array (23) are all plate-shaped and have the same size; In the launching state, the second solar cell subarray (22) and the third solar cell subarray (23) are folded together at the same side and pressed against the first solar cell subarray (21), and the third solar cell subarray (23) is located above the second solar cell subarray (22); in the on-orbit state, the third solar cell subarray (23) and the second solar cell subarray (22) are respectively unfolded to both sides around the first solar cell subarray (21), and after unfolding, the first solar cell subarray (21), the second solar cell subarray (22) and the third solar cell subarray (23) form a coplanar surface; The phased array antenna (3) comprises a first phased array antenna (31) connected to the ground-facing surface of the satellite platform (1), and a second phased array antenna (32) and a third phased array antenna (33) respectively connected to two ends of the first phased array antenna (31); the first phased array antenna (31), the second phased array antenna (32) and the third phased array antenna (33) are all plate-shaped antennas and have the same size; In the transmitting state, the second phased array antenna (32) and the third phased array antenna (33) are folded together at the same side and pressed against the first solar cell subarray (21), and the third phased array antenna (33) is located above the second phased array antenna (32); in the on-orbit state, the third phased array antenna (33) and the second phased array antenna (32) are respectively unfolded to both sides around the first phased array antenna (31), and after unfolding, the first phased array antenna (31), the second phased array antenna (32) and the third phased array antenna (33) form a coplanar surface; The electric thruster (138) comprises a mounting bracket (1381), an adjustment gasket (1382) for connecting the mounting bracket (1381) to the outside of the cabin plate of the satellite structure (11) via screws, and a thrust chamber (1383) connected to the mounting bracket (1381); The fixing positions of the mounting bracket (1381) and the adjustment gasket (1382) are adjustable, the fixing positions of the mounting bracket (1381) and the thrust chamber (1383) remain unchanged, and the mounting bracket (1381) can be adjusted with multiple degrees of freedom to install the thrust chamber (1383) through the adjustment gasket (1382) without changing the mounting interface of the satellite structure (11) to meet the attitude control accuracy requirements of the flat-panel SAR satellite; The mounting bracket (1381) comprises a mounting bracket body (13811), a mounting interface (13812) connected to the mounting bracket body (13811), and an adjustment gasket interface (13813) connected to the edge of the mounting bracket body (13811); The mounting bracket body (13811) is a plate-like structure, and the adjustment gasket interface (13813) is a stepped circular opening; The adjusting gasket (1382) comprises a first circular disc structure (13821) and a second circular disc structure (13822) which are vertically and coaxially connected, a straight slot (13823) which is connected through the center of the first circular disc structure (13821) and the second circular disc structure (13822), and circular holes (13824) which are symmetrically connected to the first circular disc structure (13821) on both sides of the straight slot (13823); the diameter of the first circular disc structure (13821) is larger than the diameter of the second circular disc structure (13822), and the straight slot (13823) is an oblong opening; The adjusting gasket (1382) can rotate 360 ​​degrees in the adjusting gasket interface (13813) to drive the straight slot (13823) to rotate, and the fixed position of the mounting bracket (1381) on the mounting cabin plate of the star structure (11) can be adjusted by rotating the adjusting gasket (1382) left and right, up and down, and forward and reverse.

2. A flat-panel SAR satellite with a standardized satellite platform according to claim 1, characterized in that: The star structure (11) is a box-type structure composed of aluminum skin honeycomb sandwich panels; The satellite structure (11) comprises a +X cabin plate (111) and a -X cabin plate (112) arranged oppositely, a +Y cabin plate (113) and a -Y cabin plate (114) arranged oppositely, a +Z cabin plate (115) and a -Z cabin plate (116) arranged oppositely, and a partition plate (117) connected between the +Y cabin plate (113) and the -Y cabin plate (114) and parallel to the +X cabin plate (111) and the -X cabin plate (112), the first solar cell sub-array (21) being connected to the -Z cabin plate (116), and the first phased array antenna (31) being connected to the +Z cabin plate (115); The +X cabin plate (111), the -X cabin plate (112), the +Y cabin plate (113), the -Y cabin plate (114), the -Z cabin plate (116), and the partition plate (117) are first assembled and then assembled with the +Z cabin plate (115).

3. A flat-panel SAR satellite with a standardized satellite platform according to claim 2, characterized in that: The subsystem assembly (13) further includes a data transmission antenna (131) connected to the outside of the cabin of the satellite structure (11), a ground telemetry and remote control antenna (132), a primary satellite sensor (133), a GNSS antenna (134), a backup satellite sensor (136), a sky telemetry and remote control antenna (137), a magnetic torquer Z (139), and a battery pack (1310), integrated electronics (1311), a high-performance computer (1312), an electric propulsion controller (1313), a momentum wheel (1314), a momentum wheel S (1315), a momentum wheel X (1316), and an electric propulsion tank (1317) connected to the cabin of the satellite structure (11). , load controller (1318), magnetic torque Y (1319), momentum wheel Z (1320), magnetic torque X (1321), data transmitter (1322), power supply controller (1323), fiber optic gyroscope (1324), magnetometer (1325); The number of the magnetic torquer Z (139) and the number of the magnetometer (1325) are both two.

4. A flat-panel SAR satellite with a standardized satellite platform according to claim 3, characterized in that: The data transmission antenna (131), the ground telemetry and remote control antenna (132), the main satellite sensor (133), the Taimin (134) and the GNSS antenna (135) are located on the same X-direction cabin panel or Y-direction cabin panel, the standby satellite sensor (136), the sky telemetry and remote control antenna (137), the electric thruster (138) and the magnetic torquer Z (139) are located on the cabin panel on the opposite side, and the thrust line of the electric thruster (138) is close to the center of mass of the flat-panel SAR satellite and does not block the plume; The connection points between the second solar cell subarray (22), the third solar cell subarray (23) and the first solar cell subarray (21), and the connection points between the second phased array antenna (32), the third phased array antenna (33) and the first phased array antenna (31) are located on a deck adjacent to the subsystem component (13).

5. The flat-panel SAR satellite with a standardized satellite platform according to claim 1, characterized in that: The mounting bracket (1381) further includes a weight-reducing opening (13814); The number of the mounting interfaces (13812) is 4 and they are symmetrically distributed. The number of the adjustment gasket interfaces (13813) and the adjustment gaskets (1382) are both four. The adjustment gasket interfaces (13813) are located at the four corners of the mounting bracket body (13811), and the mounting interfaces (13812) are distributed between the adjustment gasket interfaces (13813).

6. The flat-panel SAR satellite with a standardized satellite platform according to claim 1, characterized in that: The number of the solar cell array (2) and the phased array antenna (3) sub-arrays is greater than or equal to 3, and they are respectively gathered together at the same side and pressed tightly on the sky-facing side and the ground-facing side of the satellite platform (1).

7. A flat-panel SAR satellite with a standardized satellite platform according to any one of claims 1 to 6, characterized in that: The assembly method of the flat-panel SAR satellite comprises the following steps: S1. Assembling the +X cabin plate (111), the -X cabin plate (112), the +Y cabin plate (113), the -Y cabin plate (114), the -Z cabin plate (116), and the partition plate (117) of the star platform (1) into star structure components by means of screws; S2. Installing the subsystem stand-alone components of the satellite platform (1) onto the satellite structure components, with the inertia evenly distributed, leaving space for cable laying and meeting the technical requirements of each stand-alone component for installation; S3, installing and debugging the +Z cabin plate (115) of the satellite platform (1) and the phased array antenna (3) to obtain a phased array antenna component; S4, docking the satellite structure component and the phased array antenna component; S5. Carry out final assembly, testing and experiment of the flat-panel SAR satellite. After passing the test, a flat-panel SAR satellite with a standardized satellite platform is assembled.

8. The flat-panel SAR satellite with a standardized satellite platform according to claim 7, characterized in that: In step S3, when the size of the phased array antenna (3) needs to be changed, it is only necessary to adjust the size of the +Z cabin plate (115); In step S5, when debugging the electric thruster (138) of the satellite platform (1), the coordinates of the center of mass position of the flat-panel SAR satellite are measured by a mass testing platform, and then the coordinates of the thrust axis of the thrust chamber (1383) on the installation plane are measured, and the installation error of the thrust chamber (1383) is calculated; When the thrust chamber installation error is greater than a threshold value, the position of the thrust chamber (1383) is adjusted by: calculating the distance and orientation that the thrust chamber (1383) needs to move relative to the current installation state by comparing with the thrust chamber (1383) installation requirements proposed by the attitude control subsystem of the satellite platform (1); marking the position of the mounting bracket (1381) that needs to be adjusted on the mounting cabin plate of the satellite platform (1) with a marking pen, loosening the mounting screws on the four adjustment gaskets (1382) and rotating the adjustment angle until the mounting bracket (1381) is adjusted to the marked position, and then tightening the four mounting screws to complete the position adjustment of the thrust chamber (1383).

Images