CN113065243A - Optimization method for satellite-borne antenna layout - Google Patents

Optimization method for satellite-borne antenna layout Download PDF

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CN113065243A
CN113065243A CN202110306555.9A CN202110306555A CN113065243A CN 113065243 A CN113065243 A CN 113065243A CN 202110306555 A CN202110306555 A CN 202110306555A CN 113065243 A CN113065243 A CN 113065243A
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satellite
optimization method
borne antenna
angle
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CN113065243B (en
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卢元申
朱峪
吴敏
张文
古启军
张军
涂珍贞
祁见忠
石龙龙
王正凯
李锐
张强
何盼
王学良
习成献
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Shanghai Engineering Center for Microsatellites
Innovation Academy for Microsatellites of CAS
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    • G06F30/20—Design optimisation, verification or simulation
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
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    • H04—ELECTRIC COMMUNICATION TECHNIQUE
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    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/1851—Systems using a satellite or space-based relay
    • H04B7/18515—Transmission equipment in satellites or space-based relays
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/1851—Systems using a satellite or space-based relay
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    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service

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Abstract

The invention provides an optimization method of satellite-borne antenna layout, which comprises the steps of firstly setting an initial installation angle and a maximum iteration frequency of a satellite-borne antenna, then calculating a loss function according to the initial installation angle, judging whether a convergence condition is reached, if the convergence condition is not reached, iteratively updating the installation angle of the satellite-borne antenna according to the set initial step length, calculating the loss function again according to the updated installation angle, judging whether the convergence condition is reached, and if the convergence condition is not reached, continuing iteration until the maximum iteration frequency is reached or the convergence condition is reached.

Description

Optimization method for satellite-borne antenna layout
Technical Field
The invention relates to the technical field of aerospace, in particular to an optimization method for satellite-borne antenna layout.
Background
For a high-orbit satellite based on a full electric propulsion platform, the whole process of orbit transfer and orbit entering from a GTO orbit to a GEO orbit needs to be completed by means of self electric propulsion. However, the electric propulsion thrust is small, the satellite orbit entering time is usually as long as several months, and the earth measurement and control pointing direction is difficult to guarantee, so that the orbit transfer task is completed by depending on a space-based measurement and control network to guarantee the electric propulsion orbital transfer thrust pointing direction and the energy requirement.
For the space-based measurement and control network, the layout of the satellite-borne antenna is crucial to ensure the accuracy of the space-based measurement and control network. At present, a common Satellite-borne antenna layout method includes that firstly, a Satellite task simulation system based on a Satellite Toolkit (STK) performs feasibility analysis on a Satellite-borne antenna installation angle, and then antenna layout is performed by combining feasibility analysis results and historical experience. However, the simulation result based on the STK is usually different from the actual result, and if the satellite-borne antenna layout cannot meet the task requirement, the satellite-borne antenna layout needs to be compensated by means of increasing the number of the satellite-borne antennas or changing the antenna design, which causes precious satellite-borne resource waste and huge cost overhead, and even affects the task success or failure.
Disclosure of Invention
Aiming at partial or all problems in the prior art, the invention provides a satellite-borne antenna layout optimization method, which comprises the following steps:
setting an initialization value comprising an initial installation angle of the satellite-borne antenna and the maximum iteration number;
calculating a loss function according to the initial installation angle, and judging whether a convergence condition is reached;
if the convergence condition is not met, updating the installation angle of the satellite-borne antenna according to the set initial step length, and performing iteration;
calculating a loss function according to the updated installation angle, and judging whether a convergence condition is reached; and
if the convergence condition is not reached, iterating again until the maximum iteration times or the convergence condition is reached.
Further, the loss function is equal to the total time length of the satellite in orbit minus the time length of visibility of the destination satellite, wherein the destination satellite is the target for establishing the inter-satellite link.
Further, the visible time length of the destination satellite refers to the total time length satisfying the following conditions:
the distance from the earth center to a connecting line between the satellite and the target satellite is greater than the radius of the earth; and is
The entry level of the destination satellite receiver is greater than the acceptance threshold of the destination satellite transponder.
Further, the satellite receiver entrance level is determined according to the target satellite-borne antenna pointing vector, the satellite-borne antenna pointing vector and the relative position between the satellite and the target satellite.
Further, the convergence condition is that the gradient of the loss function is smaller than a preset value.
Further, the step size employed per iteration is different.
Further, the step size is calculated according to a least mean square adaptive algorithm (LMSprop).
The invention provides an optimization method for satellite-borne antenna layout, which is used for calculating the performance of an inter-satellite link under the condition of known satellite orbit and attitude, and determining the optimal layout of a satellite-borne antenna by using a gradient descent algorithm with the longest link building time of the inter-satellite link as a target. The present invention is based on the following insight of the inventors: in the process of orbital transfer and orbit entry of the satellite, the earth measurement and control pointing direction is difficult to ensure, and the orbit transfer task needs to be completed by a space-based measurement and control network, so the chain building time of the orbit transfer process and the space-based measurement and control satellite has a decisive influence on the success or failure of the task. The link establishment time length depends on the visible time length of the satellite to the target satellite, therefore, in the invention, the link loss condition is comprehensively considered, the calculation of the unidirectional link with smaller link margin is selected as the standard for measuring the link performance and judging whether the link is visible or not through the link loss calculation, and finally iterative convergence is carried out to obtain the optimal layout. The method is suitable for single-objective and multi-objective conditions, the convergence is fast, and the chain building time length in the early track section after optimization is obviously prolonged.
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To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
Fig. 1 is a schematic flow chart illustrating a method for optimizing a satellite-borne antenna layout according to an embodiment of the present invention;
FIG. 2 shows a satellite-borne antenna installation schematic;
fig. 3 shows a process of solving an optimal layout of a satellite-borne antenna by using the optimization method for a layout of a satellite-borne antenna according to an embodiment of the present invention under a single-target satellite condition;
FIG. 4 shows a process of solving an optimal layout of a satellite-borne antenna by using the optimization method for a satellite-borne antenna layout according to an embodiment of the present invention under a multi-objective satellite condition; and
fig. 5 is a schematic diagram showing comparison before and after optimization of an optimization method for a satellite-borne antenna layout according to an embodiment of the present invention.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
In order to improve the link establishment duration of the satellite in the orbital transfer and orbit-in stages and ensure the success of an orbit transfer task, the invention provides an optimization method of the satellite-borne antenna layout, which is used for calculating the performance of an inter-satellite link under the condition of known satellite orbit and attitude, and determining the optimal layout of the satellite-borne antenna by using a gradient descent algorithm with the longest total link establishment time of the inter-satellite link as a target. The solution of the invention is further described below with reference to the accompanying drawings of embodiments.
Fig. 1 is a flowchart illustrating a method for optimizing a satellite-borne antenna layout according to an embodiment of the present invention. As shown in fig. 1, a method for optimizing a satellite-borne antenna layout includes:
first, in step 101, initialization is performed. Setting an initial value theta of a mounting angle to be optimized0、
Figure BDA0002987958540000031
Initial step size r0And the maximum iteration times t, wherein the angle needing to be optimized refers to the installation angle theta, theta and theta of the satellite-borne antenna,
Figure BDA0002987958540000032
Taking a satellite-borne antenna installed on a satellite + Z plane as an example, the counterclockwise rotation angle of the antenna around the vector of the satellite-Y plane is recorded as an angle theta, and the rotation angle around the + Z axis is recorded as an angle theta
Figure BDA0002987958540000033
Corner, as shown in fig. 2;
next, at step 102, a loss function is calculated. Calculating a loss function f from the initial value of the installation angleloss(ii) a In one embodiment of the invention, the loss function flossEqual to the total time length N of the satellite in orbit minus the visible time length N of the target satellites：
floss＝N-Ns，
The destination satellite refers to an object for establishing an inter-satellite link, such as a relay satellite or a ground station. In one embodiment of the present invention, the visible duration of the destination satellite refers to the total duration of time satisfying the following condition:
the distance from the earth center to a connecting line between the satellite and the target satellite is greater than the radius of the earth; and is
The receiving satellite receiver entry level, which may also be referred to as the received power, is greater than an acceptance threshold of the receiving satellite transponder, and is determined based on the destination satellite on-board antenna pointing vector, the satellite on-board antenna pointing vector, and the relative position between the satellite and the destination satellite. In an embodiment of the present invention, whether a target satellite is visible or not takes into consideration a loss condition of an inter-satellite link, and a unidirectional link with a small inter-satellite link margin is selected as a standard for measuring link performance and whether the link is visible or not through inter-satellite link loss calculation, where a calculation formula of the unidirectional link is as follows:
Prec＝Plaunch+Glaunch-Llwl-Lspace-Ppol-Lrec+Grec，
wherein, PrecTo receive power, PlaunchIs the target satellite transmission power, GlaunchIs the target satellite antenna gain, LlwlIs the loss of the feed line of the target satellite transmitting antenna, Plaunch+Glaunch-LlwlAn Equivalent Isotropic Radiated Power (EIRP) for the destination satellite, which can be defined as a function of the directional vector of the destination satellite antenna and the relative position between two satellites;
Lspaceis the spatial attenuation, the specific calculation formula is:
Figure BDA0002987958540000041
wherein, L is the distance between the target satellite and the satellite, and lambda is the measurement and control communication wavelength;
Ppolis the antenna polarization loss;
Lrecis a loss of cable; and
Grecthe function is a function of the directional vector of a satellite-borne antenna of a satellite, namely a receiving antenna, and the relative position between two satellites, and can be simplified into an included angle function of the directional vector of the receiving antenna and the directional vector from the satellite position to the target satellite position, and in one embodiment of the invention, the antenna directional vector is determined according to the following steps:
first, the satellite coordinates (X) in the J2000 coordinate system are calculated from the position data of the satellite, such as the number of orbits and timeJ，YJ，ZJ) Then converted into a northeast coordinate system (X)NEG，YNEG，ZNEG)；
Next, by calculating the velocity of the satellite relative to the earth centroid in the north east coordinate system and the position information of the satellite in the north east coordinate system, three coordinate axes of the satellite orbital coordinate system (O-xyz) can be obtained, and the directional vector calculation formula of the three axes is as follows:
Figure BDA0002987958540000051
Figure BDA0002987958540000052
Figure BDA0002987958540000053
wherein the content of the first and second substances,
Figure BDA0002987958540000054
is the velocity vector of the satellite in the northeast coordinate system, which is the velocity vector for the earth's centroid;
then, according to the satellite attitude angle data at each moment, including the roll angle R, the pitch angle P and the yaw angle Y, rotating according to Euler 3-1-2 to obtain a satellite attitude matrix T ═ T at each moment1T2T3Wherein:
Figure BDA0002987958540000055
Figure BDA0002987958540000056
Figure BDA0002987958540000057
finally, the antenna is installed at a set of given angles,
Figure BDA0002987958540000058
Obtaining the direction vector of the antenna under the body coordinate system under the angle, and multiplying the attitude matrix T by the direction vector
Figure BDA0002987958540000059
Obtaining the coordinates of the antenna in a satellite orbit coordinate system, combining three basic coordinate axes of the satellite orbit coordinate system (O-xyz) obtained before, and calculating to obtain the direction vector of the satellite actually mounted with the antenna in the northeast coordinate system
Figure BDA00029879585400000510
Figure BDA00029879585400000511
Figure BDA00029879585400000512
Figure BDA00029879585400000513
Next, at step 103, it is determined whether a convergence condition is reached. Firstly, judging whether the maximum iteration number is reached, if not, judging whether a convergence condition is reached according to the loss function, if so, finishing optimization, and if not, entering step 104; in one embodiment of the invention, the convergence condition is a gradient of a loss function
Figure BDA0002987958540000061
Less than a predetermined value, said loss function gradient
Figure BDA0002987958540000062
The calculation is as follows:
Figure BDA0002987958540000063
when in use
Figure BDA0002987958540000064
And
Figure BDA0002987958540000065
when, a convergence condition is reached, where x0And y0To lock minutes, the value is related to the total length of the track, e.g., x when the total length of the track is six months0And y0Taking the value of 30 minutes;
at step 104, the parameters are updated. Updating the installation angle of the satellite-borne antenna according to the set initial step length, and returning to step 102, in one embodiment of the present invention, updating the installation angle according to a least mean square adaptive algorithm (LMSprop):
Figure BDA0002987958540000066
Figure BDA0002987958540000067
wherein the content of the first and second substances,
riin order to be the step size,
Figure BDA0002987958540000068
wherein mu is 0.9;
epsilon is a constant which prevents the introduction of divisor 0 and takes a value of 1 e-6;
and step 104 is repeated until the maximum iteration times or convergence conditions are reached, and the optimization of the antenna installation angle is completed.
In order to verify the optimization method of the satellite-borne antenna layout in the embodiment of the invention, a certain high-orbit satellite is taken as an example, and the method is adopted to optimize the antenna layout. Firstly, calculating the visibility condition of a satellite-ground link and the performance of an inter-satellite link at each moment according to the position data, the attitude angle data, the satellite demodulation threshold and the transmitting power of a satellite, the coordinates and the attitude of a target satellite, the directional gain of the target satellite and the antenna thereof and the loss constant of a cable of the satellite, wherein the position data of the satellite comprises the number of orbits, including a pitch angle, a yaw angle and a roll angle; then, optimizing and solving the optimal layout angle of the antenna by using a gradient descent algorithm, wherein the judgment standard of the total optimization scheme is a union set of the total visible arc sections of the multi-view star, and the optimization scheme is considered when the total visible duration is maximum; and the single-target optimization scheme judgment standard is that the single-target satellite is considered as the optimization scheme when the total visible time of the single-target satellite is the maximum.
FIG. 3 shows a process for solving an optimal layout of a satellite-borne antenna by using the optimization method under the condition of a single target satellite; and fig. 4 shows a process of solving the optimal layout of the space-borne antenna by using the optimization method under the condition of multiple target stars, which shows that the convergence condition can be completed very quickly by using the optimization method no matter under the condition of single target stars or multiple target stars, and the convergence effect is very good. Fig. 5 shows a comparison schematic diagram before and after optimization by using the optimization method for the satellite-borne antenna layout according to an embodiment of the present invention, and it can be seen that the link establishment duration in the early orbit segment after optimization is significantly increased.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.

Claims (8)

1. A satellite-borne antenna layout optimization method is characterized by comprising the following steps:
setting an initial installation angle and the maximum iteration times of the satellite-borne antenna;
calculating a loss function according to the initial installation angle, and judging whether a convergence condition is reached;
if the convergence condition is not met, iteratively updating the mounting angle of the satellite-borne antenna according to the set initial step length;
calculating a loss function according to the updated installation angle, and judging whether a convergence condition is reached; and
if the convergence condition is not reached, continuing the iteration until the maximum iteration times or the convergence condition is reached.
2. The optimization method of claim 1, wherein the loss function is equal to a total time duration of satellite orbits minus a time duration of visibility of a destination satellite, wherein the destination satellite is an objective of establishing an inter-satellite link.
3. The optimization method according to claim 2, wherein the length of time in which the destination satellite is visible refers to the total length of time satisfying the following condition:
the distance from the earth center to a connecting line between the satellite and the target satellite is greater than the radius of the earth; and is
The satellite receiver entry level is greater than an acceptance threshold of the satellite transponder.
4. The optimization method of claim 3, wherein the satellite receiver entry level is determined based on a destination satellite-borne antenna pointing vector, a satellite-borne antenna pointing vector, and a relative position between the satellite and the destination satellite.
5. The optimization method of claim 1, wherein the convergence condition is that a gradient of the loss function is smaller than a preset value.
6. The optimization method of claim 1, wherein the step size employed for each iteration is different.
7. The optimization method of claim 6, wherein the step size is calculated according to a least mean square adaptive algorithm.
8. The optimization method of claim 7, wherein the update of the installation angle is calculated according to the following formula:
Figure FDA0002987958530000021
Figure FDA0002987958530000022
wherein the content of the first and second substances,
for a satellite-borne antenna installed on a + Z plane of a satellite, the counterclockwise rotation angle of the satellite-Y plane vector is an angle theta, and the rotation angle of the satellite-borne antenna around the + Z axis direction is an angle
Figure FDA0002987958530000023
An angle;
flossis a loss function;
riin order to be the step size,
Figure FDA0002987958530000024
wherein mu is 0.9;
epsilon is a constant which prevents the introduction of divisor 0 and takes a value of 1 e-6; and
and lambda is the measurement and control communication wavelength.
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