Antenna layout method for communication satellite

Abstract

The invention discloses an antenna layout method for a communication satellite. The antenna layout method comprises the following steps: S1, determining directions of antennas in an unfolded state and a spatial relationship between the antennas; s2, adjusting the relationship between the assembly and the satellite platform, and ensuring that the field of view of the antenna is not shielded in an unfolded state; s3, the relation between the antennas and the satellite platform in the folded state is adjusted, and it is guaranteed that no interference exists between the antennas and between the antennas and the satellite platform in the folded state; s4, solving a rotation axis unit vector and a rotation angle of the antenna; if the first constraint judgment condition is not met, returning to the step 2; if yes, executing the step 5, and rotating according to the rotating shaft unit vector and the rotating angle to obtain a corrected layout position; 6, if the second constraint judgment condition is not met, returning to the step 2; and if yes, outputting a result. According to the method provided by the invention, the antenna layout which meets the use requirements of an antenna system, the internal space envelope of a fairing and the size limitation of a satellite platform can be obtained.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of spacecraft design, and particularly relates to an antenna layout method for a communication satellite. BACKGROUND

[0002] As a main component of the communication satellite payload, the antenna subsystem is an important carrier for signal receiving and forwarding of the communication satellite. According to the task requirements, the configurable antennas of the communication satellite include horn antennas, reflector antennas and array antennas, etc. The horn antennas are commonly used for global beams, and the reflector antennas and array antennas are commonly used for regional beams or point beams, etc. A single communication satellite usually needs to be configured with multiple antennas to meet the business requirements. In order to improve the utilization rate of the satellite layout space, the high-gain reflector antennas usually adopt a deployment mechanism, which is folded on the satellite body during satellite launch and is deployed in orbit.

[0003] At present, the main business of the communication satellite still adopts the reflector antenna to meet the requirements of different working frequency bands and different coverage areas. The businesses carried by the reflector antennas are relatively independent, so the constraints that need to be considered in the satellite layout design of this kind of antenna usually include:

[0004] 1) the space of the launch fairing;

[0005] 2) the coupling relationship between the feed and the reflector;

[0006] 3) the non-interference of the reflector deployment path;

[0007] 4) the non-occlusion of the satellite body to the field of view of the deployed antenna.

[0008] With the continuous development of satellite communication technology, the application scenarios of the communication satellite are becoming more and more rich, the functions are becoming more and more complex, the payload configurations are becoming more and more diverse, and the coupling relationship between the antennas is becoming more and more close, which puts forward new constraints on the layout design of the communication satellite:

[0009] 5) the spatial relationship between the multiple antennas after deployment.

[0010] Therefore, in order to improve the layout efficiency of the communication satellite configured with multiple antennas, a multiple antenna layout method suitable for the engineering development of the communication satellite is urgently needed to quickly form a layout scheme and fully utilize the overall satellite layout space resources, so as to improve the stow ratio of the overall satellite. SUMMARY

[0011] The technical problem of the application is to overcome the deficiencies of the prior art and provide an antenna layout method for a communication satellite, which takes the satellite platform size, the internal space envelope of the launch vehicle fairing and the spatial relationship between multiple antennas as constraint conditions, and realizes the antenna layout design of the communication satellite that meets the antenna system use requirements, the internal space envelope of the launch vehicle fairing and the satellite platform size limitation.

[0012] To solve the above technical problems, the application discloses an antenna layout method for a communication satellite, comprising:

[0013] Step 1, according to a given selection, the pointing of each antenna to be laid out in an unfolded state and the spatial relationship between each antenna to be laid out are determined; wherein the given selection comprises a launch vehicle selection, a satellite platform selection and an antenna to be laid out selection;

[0014] Step 2, regarding each antenna to be laid out in the unfolded state as a combination, the spatial relationship between the combination and the satellite platform is adjusted to ensure that the field of view of each antenna to be laid out in the unfolded state is not blocked;

[0015] Step 3, according to the internal space envelope size of the fairing, the spatial relationship between each antenna to be laid out in the folded state and the satellite platform is adjusted to ensure that there is no interference between each antenna to be laid out in the folded state and between the antenna to be laid out and the satellite platform;

[0016] Step 4, the rotation axis unit vector of each antenna to be laid out and the rotation angle from the folded state to the unfolded state are solved, and it is determined whether the first constraint judgment condition is met; wherein if the first constraint judgment condition is not met, step 2 is returned to adjust the spatial relationship between the combination and the satellite platform again; if the first constraint judgment condition is met, step 5 is executed;

[0017] Step 5, each antenna to be laid out in the unfolded state is rotated according to the rotation axis unit vector and the rotation angle from the folded state to the unfolded state obtained in step 4 to obtain a corrected layout position;

[0018] Step 6, it is judged whether the corrected layout position meets the second constraint judgment condition; wherein if the second constraint judgment condition is not met, step 2 is returned to adjust the spatial relationship between the combination and the satellite platform again; if the second constraint judgment condition is met, the corrected layout position obtained in step 5 is taken as the final antenna layout output.

[0019] In the above antenna layout method for a communication satellite, further comprising: establishing a satellite platform body coordinate system O-XYZ, an antenna body coordinate system O i -X i Y i Z i and a combination coordinate system O0-X0Y0Z0; wherein the satellite platform body coordinate system O-XYZ is defined as follows: the theoretical center of the satellite-rocket separation surface is taken as the origin O; the positive direction of the OX axis points to the east plate of the satellite platform from the origin O; the positive direction of the OY axis points to the south plate of the satellite platform from the origin O; the OZ axis forms a right-hand system with the OX axis and the OZ axis; the antenna body coordinate system O i -X i Yi Z i The definition is as follows: with the focal point of the reflecting surface as the origin O i ; with the line-of-sight direction of the antenna to be deployed as O i Z i The positive direction of the axis; O i X i Y i plane and O i Z i Axis perpendicular, O i Y i Shaft, O i X i Axis and O i Z i The axes are in a right-handed coordinate system; the subscript i indicates the number of the antenna to be deployed; to distinguish between the deployed and retracted states of the antenna, in the antenna coordinate system O... i -X i Y i Z i Based on this, the coordinate system of each antenna to be deployed in the unfolded state is denoted as the first antenna body coordinate system O. id -X id Y id Z id The coordinate system of each antenna to be deployed in the retracted state is denoted as the second antenna body coordinate system O. is -X is Y is Z is The combined coordinate system O0-X0Y0Z0 is defined as follows: Taking any antenna body coordinate system O... i -X i Y i Z i Origin i The origin is O0; the O0X0 axis is in the same direction as the OX axis; the O0Z0 axis is in the same direction as the OZ axis; the O0Y0 axis is in the same direction as the OY axis, forming a right-handed system with the O0X0 axis and the O0Z0 axis.

[0020] In the antenna layout method for communication satellites described above, in step 1, the orientation of each antenna to be laid out in the deployed state refers to: the coordinate system O of the first antenna body. id -X id Y id Z id O id Z id The angle between the axis and the OZ axis of the satellite platform's body coordinate system O-XYZ; the spatial relationship between each antenna to be deployed in the deployed state, including: the distance relationship and angular relationship between each antenna to be deployed in the deployed state; wherein, the distance relationship between each antenna to be deployed in the deployed state is through the first antenna body coordinate system O id -Xid Y id Z id origin O id indirectly represented in the satellite platform body coordinate system O-XYZ; the angle relationship between the antennas to be laid out in the unfolded state is indirectly represented by the first antenna body coordinate system O id -X id Y id Z id direction cosine matrix A id relative to the satellite platform body coordinate system O-XYZ.

[0021] In the above antenna layout method for a communication satellite, in step 2, whether the field of view of each antenna to be laid out in the unfolded state is blocked is checked by simplifying the field of view of each antenna to be laid out into a cone; wherein the apex of the cone is at the origin O id , the axis of the cone is the pointing direction of the antenna to be laid out, and the cone angle is α; it is checked whether there is interference between the cone and the star body, and between the cones; if there is no interference between the cone and the star body, and between the cones, it is determined that the field of view of each antenna to be laid out in the unfolded state is not blocked; otherwise, it is determined that the field of view is blocked.

[0022] In the above antenna layout method for a communication satellite, in step 3, the spatial relationship between each antenna to be laid out and the satellite platform in the folded state includes: the distance relationship and the angle relationship between each antenna to be laid out and the satellite platform in the folded state; wherein the distance relationship between each antenna to be laid out and the satellite platform in the folded state is indirectly represented by the position of the origin O is -X is Y is Z is of the second antenna body coordinate system O is in the satellite platform body coordinate system O-XYZ; the angle relationship between each antenna to be laid out and the satellite platform in the folded state is indirectly represented by the direction cosine matrix A is -X is Y is Z is relative to the satellite platform body coordinate system O-XYZ. is

[0023] In the above antenna layout method for a communication satellite, in step 4, the rotation axis unit vector of each antenna to be laid out and the rotation angle from the folded state to the unfolded state are solved by using the Rodrigues rotation formula;

[0024] The Rodrigues rotation formula is expressed as follows:

[0025]

[0026] ​Among them, R i Represents the direction cosine matrix A id Transformed to the direction cosine matrix A is The rotation matrix, I denotes the identity matrix, θ i k represents the rotation angle of the antenna to be deployed. i K represents the unit vector of the rotation axis of the antenna to be deployed. i Indicates k i The antisymmetric matrix;

[0027] Then we have:

[0028]

[0029] θ i =cos -1 ((trace(R i )-1)÷2)··· (3)

[0030] θ i ≠0° and θ i ≠180°, L i =(R i -R i T )÷2÷sinθ i ··· (4)

[0031] k i =[L i (3,2)L i (1,3)L i (2,1)] T ··· (5)

[0032] Among them, trace(R) i ) represents R i traces, L i L represents the matrix used in the calculation process. i (3,2) represents matrix L i The value in the 3rd row and 2nd column, L i (1,3) represents matrix L i The value in the 1st row and 3rd column, L i (2,1) represents matrix L i The value in the second row and first column.

[0033] In the antenna layout method for communication satellites described above, in step 4, if point P satisfies: i Within the internal space envelope of the fairing, and point P i With the origin O is The connection P i O isIf the satellite platform is not interfered, it is determined that the first constraint condition is satisfied; otherwise, it is determined that the first constraint condition is not satisfied; wherein the point P i is the intersection point of the rotation plane and the rotation axis of the origin O id -X id Y id Z id of the first antenna body coordinate system O-XYZ. id

[0034] In the above antenna layout method for a communication satellite, if and 0≤z i ≤YH i , it is determined that the point P i is in the internal space envelope of the fairing; otherwise, it is determined that the point P i is not in the internal space envelope of the fairing; wherein (x i , y i , z i ) represents the coordinates of the point P i in the satellite platform body coordinate system O-XYZ, YL i represents the internal diameter of the fairing at the height z i , and YH represents the internal space height of the fairing at the position (x i , y i ).

[0035] In the above antenna layout method for a communication satellite, in step 6, if the following conditions are met: the satellite platform is not interfered by the rotation path, the envelope during the antenna rotation, and the interference between each antenna and the satellite platform determined based on the corrected layout position, it is determined that the second constraint condition is satisfied; otherwise, it is determined that the second constraint condition is not satisfied.

[0036] In the above antenna layout method for a communication satellite, the following checks are realized through the corresponding interference checking function in the three-dimensional model software: occlusion check of the field of view of each antenna to be laid out in the unfolded state, interference check between each antenna to be laid out and the satellite platform in the folded state, interference check between the line P i O is and the satellite platform, interference check between the rotation path, the envelope during the antenna rotation, and the satellite platform, and interference check between each antenna and the satellite platform determined based on the corrected layout position.

[0037] The present application has the following advantages:

[0038] (1) The present application discloses an antenna layout method for a communication satellite, which is suitable for all unfolded antenna layout design processes.

[0039] ​(2) The application discloses an antenna layout method for a communication satellite, which can quickly provide a feasible solution of antenna layout and shorten a design period.

[0040] (3) The application discloses an antenna layout method for a communication satellite, which can quickly adjust the antenna layout based on iterative solution, optimize layout space of the whole satellite and improve a storage ratio of the whole satellite layout. BRIEF DESCRIPTION OF DRAWINGS

[0041] Figure 1 is a flow chart of an antenna layout method for a communication satellite in an embodiment of the application;

[0042] Figure 2 is a definition of a satellite platform body coordinate system and a size marking diagram of a satellite platform in an embodiment of the application;

[0043] Figure 3 is an internal space envelope size diagram of a fairing of a carrier rocket in an embodiment of the application;

[0044] Figure 4 is a diagram of an antenna body coordinate system in an embodiment of the application;

[0045] Figure 5 is a constraint relationship diagram between antennas in an embodiment of the application;

[0046] Figure 6 is a diagram of a combination body coordinate system in an embodiment of the application;

[0047] Figure 7 is a relative position diagram between a combination body and a satellite platform in an embodiment of the application;

[0048] Figure 8 is a diagram of a satellite loading state of an antenna in an embodiment of the application;

[0049] Figure 9 is a diagram of a satellite loading state of an antenna after correction in an embodiment of the application. DETAILED DESCRIPTION

[0050] To make the purpose, technical scheme and advantages of the application clearer, the following will further describe the disclosed embodiments of the application in combination with the drawings.

[0051] Reference Figure 1 In the embodiment, the antenna layout method for the communication satellite comprises the following steps.

[0052] Step 1, according to given selection, determining the pointing of each antenna to be laid out in an unfolded state and the spatial relationship between the antennas to be laid out.

[0053] In the present embodiment, the following several types of coordinates are mainly involved:

[0054] Satellite platform body coordinate system O-XYZ: taking the theoretical center of the satellite-rocket separation surface as the origin O; the positive direction of the OX axis points to the east plate of the satellite platform from the origin O; the positive direction of the OY axis points to the south plate of the satellite platform from the origin O; the OZ axis forms a right-hand system with the OX axis and the OZ axis.

[0055] Antenna body coordinate system O i -X i Y i Z i : taking the focal point of the reflecting surface as the origin O i ; taking the boresight direction of the antenna to be laid out as the positive direction of the O i Z i axis; the O i X i Y i plane is perpendicular to the O i Z i axis, the O i Y i axis and the O i X i axis form a right-hand system with the O i Z i axis. Among them, the subscript i represents the number of the antenna to be laid out. In order to distinguish between the unfolded state and the folded state of the antenna to be laid out, on the basis of the antenna coordinate system O i -X i Y i Z i , the body coordinate system of each antenna to be laid out in the unfolded state is denoted as the first antenna body coordinate system O id -X id Y id Z id , and the body coordinate system of each antenna to be laid out in the folded state is denoted as the second antenna body coordinate system O is -X is Y is Z is .

[0056] Combined body coordinate system O0-X0Y0Z0: taking the origin O i -X i Y i Z i of any antenna body coordinate system O i as the origin O0; the O0X0 axis is consistent with the direction of the OX axis; the O0Z0 axis is consistent with the direction of the OZ axis; the O0Y0 axis is consistent with the direction of the OY axis, and the O0Y0 axis, the O0X0 axis and the O0Z0 axis form a right-hand system.

[0057] Preferably, the launch vehicle type, the satellite platform type and the antenna type to be laid out are given in advance, and then the pointing of each antenna to be laid out in the deployed state and the spatial relationship between the antennas to be laid out are determined on this basis. The pointing of each antenna to be laid out in the deployed state refers to the angle between the axis of the antenna to be laid out and the OZ axis. id Z id The angle between the axis of the antenna to be laid out and the OZ axis. The spatial relationship between the antennas to be laid out in the deployed state includes the distance relationship and the angle relationship between the antennas to be laid out in the deployed state. The distance relationship between the antennas to be laid out in the deployed state is indirectly represented by the position of the first antenna body coordinate system O id in the satellite platform body coordinate system O-XYZ. The angle relationship between the antennas to be laid out in the deployed state is indirectly represented by the direction cosine matrix A id of the first antenna body coordinate system O id in the satellite platform body coordinate system O-XYZ. id Z id with respect to the satellite platform body coordinate system O-XYZ. id .

[0058] Step 2: The antennas to be laid out in the deployed state are regarded as a combination, and the spatial relationship between the combination and the satellite platform is adjusted to ensure that the field of view of each antenna to be laid out in the deployed state is not blocked.

[0059] In this embodiment, whether the field of view of each antenna to be laid out in the deployed state is blocked can be checked in the following manner: In the antenna layout design stage of the communication satellite, the field of view of each antenna to be laid out can be simplified as a cone, the vertex of the cone is at the origin O id , the axis is the pointing of the antenna to be laid out, and the cone angle is a. Further, whether there is interference between the cone and the satellite body and between the cones can be checked by the corresponding interference checking function in the three-dimensional model software. If there is no interference between the cone and the satellite body and between the cones, it is determined that the field of view of each antenna to be laid out in the deployed state is not blocked. Otherwise, it is determined that the field of view is blocked.

[0060] Step 3: According to the internal space envelope size of the fairing, the spatial relationship between each antenna to be laid out and the satellite platform in the stowed state is adjusted to ensure that there is no interference between each antenna to be laid out and between the antenna to be laid out and the satellite platform in the stowed state.

[0061] In this embodiment, the spatial relationship between each antenna to be laid out and the satellite platform in the stowed state includes the distance relationship and the angle relationship between each antenna to be laid out and the satellite platform in the stowed state. The distance relationship between each antenna to be laid out and the satellite platform in the stowed state is indirectly represented by the position of the first antenna body coordinate system O is in the satellite platform body coordinate system O-XYZ. The angle relationship between each antenna to be laid out and the satellite platform in the stowed state is indirectly represented by the direction cosine matrix A is of the first antenna body coordinate system O isY is Z is Direction cosine matrix A of satellite platform body coordinate system O-XYZ is An indirect representation is made.

[0062] It should be noted that the interference check between each antenna to be laid out and between the antenna to be laid out and the satellite platform in the folded state can be realized by the corresponding interference check function in the three-dimensional model software.

[0063] Step 4, solving the rotation axis unit vector of each antenna to be laid out and the rotation angle from the folded state to the unfolded state, and determining whether the first constraint condition is satisfied.

[0064] In this embodiment, the rotation axis unit vector of each antenna to be laid out and the rotation angle from the folded state to the unfolded state can be solved by using the Rodrigues rotation formula.

[0065] The Rodrigues rotation formula is expressed as follows:

[0066]

[0067] wherein R i represents the rotation matrix of direction cosine matrix A id transformed to direction cosine matrix A is , I represents the unit matrix, θ i represents the rotation angle of the antenna to be laid out, k i represents the rotation axis unit vector of the antenna to be laid out, K i represents the skew-symmetric matrix of k i .

[0068] Then, we have:

[0069]

[0070] θ i = cos -1 ((trace(R i )-1)÷2)··· (3)

[0071]

[0072] k i =[L i (3,2)L i (1,3)L i (2,1)] T ··· (5)

[0073] wherein trace(R i ) represents the trace of R i , L iL represents the matrix used in the calculation process. i (3,2) represents matrix L i The value in the 3rd row and 2nd column, L i (1,3) represents matrix L i The value in the 1st row and 3rd column, L i (2,1) represents matrix L i The value in the second row and first column.

[0074] Furthermore, if the following conditions are met: point P i Within the internal space envelope of the fairing, and point P i With the origin O is The connection P i O is If there is no interference with the satellite platform, then the first constraint condition is met, and step 5 is executed. Otherwise, the first constraint condition is not met, and the process returns to step 2 to readjust the spatial relationship between the assembly and the satellite platform. Wherein, point P... i For: passing through the first antenna body coordinate system O id -X id Y id Z id Origin id The intersection of the plane of rotation and the axis of rotation.

[0075] Furthermore, point P can be determined in the following way. i Whether it is within the internal space envelope of the fairing: If And 0≤z i ≤YH i Then point Pi is determined to be within the internal space envelope of the fairing. Where (x i ,y i ,z i ) represents point P i The coordinates in the satellite platform's body coordinate system O-XYZ, YL i This indicates that the fairing is at height z i The internal diameter at the location, YH represents the fairing within (x i ,y i The height of the internal space at the location.

[0076] It should be noted that the connection P i O is Interference checks with satellite platforms can be performed using the corresponding interference check function in 3D modeling software.

[0077] Step 5: Rotate each antenna to be deployed in the deployed state according to the unit vector of the rotation axis obtained in Step 4 and the rotation angle from the folded state to the deployed state to obtain the corrected deployment position.

[0078] Step 6: Determine whether the corrected layout position meets the second constraint judgment condition.

[0079] In this embodiment, if the second constraint determination condition is not met, the process returns to step 2 and the spatial relationship between the assembly and the satellite platform is readjusted; if the second constraint determination condition is met, the corrected layout position obtained in step 5 is used as the final antenna layout output.

[0080] Preferably, the satisfaction of the second constraint criterion can be determined in the following manner:

[0081] If the following conditions are met: there is no interference between the rotation path, the antenna envelope during the rotation process and the satellite platform, and there is no interference between the antennas and between the antennas and the satellite platform as determined based on the corrected layout positions, then the second constraint condition is satisfied; otherwise, the second constraint condition is not satisfied.

[0082] It should be noted that the rotation path and the envelope during antenna rotation can be determined by 3D modeling software, and the interference situation can be realized through the corresponding interference checking function in the 3D modeling software.

[0083] Based on the above embodiments, the following is an explanation with reference to a specific example.

[0084] like Figure 2 As shown, the basic dimensions of the selected satellite platform are as follows: length L = 3000mm, width B = 3000mm, height H = 7000mm. Figure 3 As shown, the internal space envelope dimensions of the selected launch vehicle fairing are as follows: diameter YL1 = 5000mm, diameter YL2 = 3500mm at different heights within the internal space; and heights YH1 = 8000mm, YH2 = 9500mm at different heights within the internal space. Figure 4 As shown, the antenna to be deployed consists of 5 reflector antennas with a diameter of D = 500 mm, and the simplified antenna field of view cone angle α = 10°.

[0085] like Figure 5 As shown, the origin O of the coordinate system of the five antennas in the deployed state is... 1d ~O 5d Coplanar, O id Z id The axes all make a 30° angle with the OZ axis, with the origin O. 3d For connecting line O 1d O 5d With line O 2d O 4d The intersection point, O 1d O 3d =O 4d O 3d=5000mm, O 2d O 3d =O 5d O 3d =3000mm.

[0086] Based on the relative positions of the five antennas, the origin O0 of the combined coordinate system is connected to the origin O of the body coordinate system of antenna 3. 3d Overlap, such as Figure 6 As shown. To reduce the deployment mechanism, antenna 3 is directly mounted on the satellite platform. The relative positions of the assembly and the satellite platform are as follows. Figure 6 , Figure 7 As shown in Table 1, the relationships between the coordinate systems of each antenna body and the coordinate system of the satellite platform body in the deployed state are as follows:

[0087]

[0088] Table 1

[0089] The interference check function of the 3D model software confirmed that the field of view of each antenna was not obstructed.

[0090] like Figure 8 As shown in Table 2, based on the available space on the satellite platform, antennas 1, 2, 4, and 5 are folded up on the X side of the satellite platform. The relationship between the coordinate system of each antenna body and the coordinate system of the satellite platform body in the folded-up state is shown in Table 2.

[0091]

[0092] Table 2

[0093] Interference checking function of 3D modeling software confirmed that there was no interference between antennas or between antennas and satellite platform.

[0094] Using the formulas (1) to (5) above, the unit vectors and rotation angles of the rotation axes of antennas 1, 2, 4, and 5 are obtained. The spatial positions of the rotation axes are determined according to the geometric relationships. The rotation axes and rotation angles of each antenna in the satellite platform body coordinate system are shown in Table 3.

[0095]

[0096] Table 3

[0097] Point P i satisfy That is, within the internal space envelope of the fairing, and determined by the interference check function of 3D modeling software, the connection P is... i O is There is no interference with the satellite platform.

[0098] The antennas 1, 2, 4, 5 in the unfolded state are retracted according to Table 3, a three-dimensional model software is modeled and interference checking is performed, the retraction path and the antenna rotation envelope do not interfere with the satellite platform, and a modified layout position is obtained, as shown in Table 4. Figure 9 In the retracted state, there is no interference between the antennas and between the antennas and the satellite platform, and the relationship between the coordinate system of each antenna body and the coordinate system of the satellite platform in the modified retracted state is shown in Table 4.

[0099]

[0100]

[0101] Table 4

[0102] The compatibility between the modified layout and the internal space of the fairing meets the requirements, that is, a feasible antenna layout scheme that meets the constraints is obtained.

[0103] Although the present application has been disclosed with the above preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents without departing from the spirit and scope of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not deviate from the technical solutions of the present application, shall fall within the protection scope of the technical solutions of the present application.

[0104] The contents not described in detail in the specification of the present application are known to those skilled in the art.

Claims

1. An antenna layout method for communication satellites, characterized in that, include: Step 1: Based on the given selection, determine the orientation of each antenna to be deployed in the deployed state and the spatial relationship between each antenna; whereby the given selection includes: launch vehicle selection, satellite platform selection, and antenna selection. Step 2: Treat each antenna to be deployed in the deployed state as an assembly, and adjust the spatial relationship between the assembly and the satellite platform to ensure that the field of view of each antenna to be deployed in the deployed state is not blocked. Step 3: Based on the internal space envelope size of the fairing, adjust the spatial relationship between each antenna to be deployed and the satellite platform in the folded state to ensure that there is no interference between each antenna to be deployed and between the antenna to be deployed and the satellite platform in the folded state. Step 4: Solve for the unit vector of the rotation axis of each antenna to be deployed and the rotation angle from the folded state to the unfolded state, and determine whether the first constraint judgment condition is met; if the first constraint judgment condition is not met, return to step 2 and readjust the spatial relationship between the assembly and the satellite platform; if the first constraint judgment condition is met, proceed to step 5. Step 5: Rotate each antenna to be deployed in the deployed state according to the unit vector of the rotation axis obtained in Step 4 and the rotation angle from the folded state to the deployed state to obtain the corrected deployment position. Step 6: Determine whether the corrected layout position meets the second constraint judgment condition; if the second constraint judgment condition is not met, return to step 2 and readjust the spatial relationship between the assembly and the satellite platform; if the second constraint judgment condition is met, the corrected layout position obtained in step 5 is used as the final antenna layout output.

2. The antenna layout method for communication satellites according to claim 1, characterized in that, Also includes: Establish the satellite platform body coordinate system O-XYZ and the antenna body coordinate system O i -X i Y i Z i The coordinate system is O0-X0Y0Z0; where the satellite platform's body coordinate system O-XYZ is defined as follows: the origin O is the theoretical center of the circle on the satellite-rocket separation surface; the positive direction of the OX axis points from the origin O to the east plate of the satellite platform; the positive direction of the OY axis points from the origin O to the south plate of the satellite platform; the OZ axis forms a right-handed system with the OX and OZ axes; the antenna body coordinate system O... i -X i Y i Z i The definition is as follows: with the focal point of the reflecting surface as the origin O. i ; with the line-of-sight direction of the antenna to be deployed as O i Z i The positive direction of the axis; O i X i Y i Plane and O i Z i Axis perpendicular, O i Y i Shaft, O i X i Shaft and O i Z i The axes are in a right-handed coordinate system; the subscript i indicates the number of the antenna to be deployed; to distinguish between the deployed and retracted states of the antenna, in the antenna coordinate system O... i -X i Y i Z i Based on this, the coordinate system of each antenna to be deployed in the unfolded state is denoted as the first antenna body coordinate system O. id -X id Y id Z id The coordinate system of each antenna to be deployed in the retracted state is denoted as the second antenna body coordinate system O. is -X is Y is Z is The coordinate system O0-X0Y0Z0 of the combined body is defined as follows: Taking any antenna body coordinate system O... i -X i Y i Z i Origin i The origin is O0; the O0X0 axis is in the same direction as the OX axis; the O0Z0 axis is in the same direction as the OZ axis; the O0Y0 axis is in the same direction as the OY axis, forming a right-handed system with the O0X0 axis and the O0Z0 axis.

3. The antenna layout method for communication satellites according to claim 2, characterized in that, In step 1, the orientation of each antenna to be deployed in the unfolded state refers to: the coordinate system O of the first antenna body. id -X id Y id Z id O id Z id The angle between the axis and the OZ axis of the satellite platform's body coordinate system O-XYZ; The spatial relationships between the antennas to be deployed in the deployed state include: the distance and angular relationships between the antennas to be deployed in the deployed state; wherein, the distance relationships between the antennas to be deployed in the deployed state are defined by the first antenna body coordinate system O. id -X id Y id Z id Origin id The positions are indirectly represented in the satellite platform's coordinate system O-XYZ; the angular relationships between the antennas to be deployed in the deployed state are represented by the first antenna body coordinate system O. id -X id Y id Z id The direction cosine matrix A relative to the satellite platform's body coordinate system O-XYZ id Indirect representation.

4. The antenna layout method for communication satellites according to claim 1, characterized in that, In step 2, the field of view of each antenna to be deployed in the deployed state is checked as follows: the field of view of each antenna to be deployed is simplified to a cone; wherein the vertex of the cone is at the origin O. id The axis of the cone points to the antenna to be deployed, and the cone angle of the cone is α. Check whether there is interference between the cone and the star, and between the cone itself. If there is no interference between the cone and the star, and between the cone itself, then it is determined that the field of view of each antenna to be deployed is not blocked in the deployed state; otherwise, it is determined that the field of view is blocked.

5. The antenna layout method for communication satellites according to claim 3, characterized in that, In step 3, the spatial relationship between each antenna to be deployed and the satellite platform in the folded state includes: the distance and angular relationship between each antenna to be deployed and the satellite platform in the folded state; wherein, the distance relationship between each antenna to be deployed and the satellite platform in the folded state is determined through the second antenna body coordinate system O. is -X is Y is Z is Origin is The positions are indirectly represented in the satellite platform's body coordinate system O-XYZ; the angular relationships between each antenna to be deployed and the satellite platform in the retracted state are represented in the second antenna body coordinate system O. is -X is Y is Z is The direction cosine matrix A relative to the satellite platform's body coordinate system O-XYZ is Indirect representation.

6. The antenna layout method for a communication satellite according to claim 5, characterized in that, In step 4, the unit vector of the rotation axis of each antenna to be deployed and the rotation angle from the folded state to the unfolded state are obtained by using the Rodriguez rotation formula. The Rodrigues rotation formula is expressed as follows: Among them, R i Represents the direction cosine matrix A id Transformed to the direction cosine matrix A is The rotation matrix, I denotes the identity matrix, θ i k represents the rotation angle of the antenna to be deployed. i K represents the unit vector of the rotation axis of the antenna to be deployed. i Indicates k i The antisymmetric matrix; Then we have: i i =cos -1 ((trace(R i )-1)÷2)···(3) k i =[L i (3.2)L i (1.3)L i (2,1)] T ···(5) Among them, trace(R) i ) represents R i traces, L i L represents the matrix used in the calculation process. i (3,2) represents matrix L i The value in the 3rd row and 2nd column, L i (1,3) represents matrix L i The value in the 1st row and 3rd column, L i (2,1) represents matrix L i The value in the second row and first column.

7. The antenna layout method for communication satellites according to claim 2, characterized in that, In step 4, if the following conditions are met: point P i Within the internal space envelope of the fairing, and point P i With the origin O is The connection P i O is If there is no interference with the satellite platform, then the first constraint condition is met. Otherwise, it is determined that the first constraint condition is not met; where point P i For: passing through the first antenna body coordinate system O id -X id Y id Z id Origin id The intersection of the plane of rotation and the axis of rotation.

8. The antenna layout method for a communication satellite according to claim 7, characterized in that, like And 0≤z i ≤YH i Then point P is determined. i Within the internal space envelope of the fairing; otherwise Determine point P i Not within the internal space envelope of the fairing; where, (x i ,y i ,z i ) represents point P i The coordinates in the satellite platform's body coordinate system O-XYZ, YL i This indicates that the fairing is at height z i The internal diameter at the location, YH represents the fairing within (x i ,y i The height of the internal space at the location.

9. The antenna layout method for a communication satellite according to claim 7, characterized in that, In step 6, if the following conditions are met: there is no interference between the rotation path, the envelope of the antenna during rotation, and the satellite platform, and there is no interference between the antennas and between the antennas and the satellite platform as determined based on the corrected layout position, then the second constraint judgment condition is satisfied. Otherwise, the second constraint condition is not met.

10. The antenna layout method for a communication satellite according to claim 9, characterized in that, The following checks are performed using the corresponding interference checking function in the 3D modeling software: obstruction checks of the field of view of each antenna to be deployed in the deployed state; interference checks between each antenna to be deployed and between the antenna to be deployed and the satellite platform in the retracted state; and connection P. i O is Interference checks with the satellite platform, interference checks between the antenna and the satellite platform during the rotation path and antenna rotation process, and interference checks between antennas and the satellite platform based on the corrected layout positions.

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