CN112278322A - Marine satellite regression orbit determination method and device and storage medium - Google Patents

Marine satellite regression orbit determination method and device and storage medium Download PDF

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CN112278322A
CN112278322A CN202011158315.0A CN202011158315A CN112278322A CN 112278322 A CN112278322 A CN 112278322A CN 202011158315 A CN202011158315 A CN 202011158315A CN 112278322 A CN112278322 A CN 112278322A
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period
orbit
aliasing
tide
satellite
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CN112278322B (en
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眭晓虹
刘波
袁春柱
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China Academy of Space Technology CAST
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories

Abstract

The application discloses a method and a device for determining a marine satellite regression orbit and a storage medium, wherein the method comprises the following steps: determining the minimum regression days for realizing global full coverage of satellites with different swaths according to the observation width of the satellites and the number of running turns in the revisiting period; determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite according to the minimum regression days and the orbit parameters of the satellite; carrying out tide aliasing analysis according to each partial tide of the tide, determining a tide aliasing equation, substituting the satellite orbit regression cycle into the tide aliasing equation, and calculating the aliasing cycle of each partial tide; calculating a convergence period between the chaos aliasing signals of each partial tide based on the aliasing period of each partial tide; and judging whether the aliasing period of each tide can be divided or not, and if the aliasing period of each tide can not be divided, re-determining the orbit height, the orbit inclination angle, the intersection point period, the satellite operation circle number and the satellite orbit regression period of the satellite until determining the relevant parameters of the suitable ocean satellite regression orbit as the design parameters.

Description

Marine satellite regression orbit determination method and device and storage medium
Technical Field
The embodiment of the application relates to a method and a device for determining a marine satellite regression orbit and a storage medium.
Background
Ocean satellite remote sensing is an effective means for investigating, monitoring and observing the ocean dynamic environment and ocean water color information. By carrying the effective loads such as a radar altimeter, a microwave radiometer, a microwave scatterometer, a real aperture radar, a synthetic aperture radar, a camera and the like, ocean dynamic environment parameters such as wind, wave, vortex, tide, flow and the like of ocean and water color parameters such as sea ice, water quality, temperature, red tide, ocean fishing ground environment, coastal zone environment and the like can be observed.
Ocean tides have a great influence on the marine productive life of mankind, who are trying to understand and qualitatively describe the tidal phenomenon and its changing laws. With the development of marine satellite remote sensing technology, how to separate and extract tidal signals from satellite observation signals and how to acquire harmonic parameters of each tide of tide become important issues to be paid attention to by researchers. The development of satellite marine height measurement technology plays a crucial role in tide research, and the tide phenomenon which cannot be prompted by the traditional shore-based discrete observation is reflected from the global perspective. The satellite altimetry system can systematically provide the tide parameter distribution on the satellite subsatellite point track. However, the case where tidal separation or prolonged separation is inseparable due to tidal aliasing is not sufficiently appreciated.
Tidal aliasing is the result of satellite shortages in the tidal sampling rate. The tide is formed by overlapping tide components. Since the main tide of the tide is full or half-day tide, the signal period is one day or half day, and the frequency is about 1cycle/d or 2 cycle/d. According to the sampling theorem, if the tidal signal is to be extracted, the lowest observed frequency is the Nyquist frequency, i.e., twice the respective partial tide frequency. For a fixed sea point, the sampling interval of the satellite to the sea surface is the regression period of the orbit. Launched marine series satellites HY-1 and HY-2 run on a sun synchronous orbit with an orbit inclination angle of about 98 degrees, and the tide aliasing phenomenon is serious. Taking HY-2 satellite as an example, the orbital regression period is 14 days, and the highest frequency of the extracted signals is 0.0020cycle/d, i.e. HY-2 satellite data on the surface can only be used for analyzing low-frequency and long-period ocean variation parameters. Obviously, for half-and full-time tides with periods of mainly half-or one-day, this sampling frequency does not allow to reconstruct the original tidal signal as above.
Disclosure of Invention
In view of this, embodiments of the present application provide a method and an apparatus for determining a marine satellite regression orbit, and a storage medium.
According to a first aspect of the present application, there is provided a method for determining a marine satellite regression orbit, comprising:
determining the minimum regression days for realizing global full coverage of satellites with different swaths according to the observation width of the satellites and the number of running turns in the revisiting period;
determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite according to the minimum regression days and the orbit parameters of the satellite;
carrying out tide aliasing analysis according to each partial tide of the tide, determining a tide aliasing equation, substituting the satellite orbit regression cycle into the tide aliasing equation, and calculating the aliasing cycle of each partial tide;
calculating a convergence period between the chaos aliasing signals of each partial tide based on the aliasing period of each partial tide;
judging whether the aliasing period of each partial tide can be divided, if the aliasing period of each partial tide can not be divided, re-determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite, and re-calculating the aliasing period of each partial tide and the convergence period of aliasing signals of each partial tide until the aliasing period of each partial tide can be divided;
if the aliasing period of each partial tide can be divided, determining the satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number according to the operation mode of the intersection period and the rising intersection right ascension precession angular velocity, and taking the determined satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number as the regression orbit design parameters of the marine satellite.
Preferably, the intersection period TNThe operation formula of (1) is as follows:
Figure BDA0002743472440000021
the rising point right ascension precession angular velocity
Figure BDA0002743472440000022
The operation formula of (1) is as follows:
Figure BDA0002743472440000031
wherein a is the distance from the satellite to the geocentric; j2 is J2 perturbation force; re6378km, earth mean radius; mu-398600.5 km3/s2I is the orbit inclination angle, and e is the orbit eccentricity.
Preferably, the calculating the aliasing period of each partial tide comprises:
for a sea surface periodic variation signal with the angular velocity sigma, the phase angle variation of a certain tide between two continuous sampling of the satellite is as follows:
Figure BDA0002743472440000032
wherein T is a satellite orbit regression period,
Figure BDA0002743472440000033
the part of tide phase change in a revisit period is less than a whole week, and n is an integer;
determination of the aliasing frequency f bya：
Figure BDA0002743472440000034
Aliasing period T of partial tideaComprises the following steps:
Figure BDA0002743472440000035
in the formula, mod represents the remainder, TaThe calculation is carried out in an interval of-180 degrees to 180 degrees.
Preferably, the calculating a convergence period between the partial tide aliasing signals based on the aliasing period of the partial tide includes:
convergence period T between two tidal aliasing signalsQComprises the following steps:
Figure BDA0002743472440000036
wherein, TaiFor the period of the partial tide aliasing signal i, TajFor the period of the partial tide aliasing signal j, take fa＝365/TaRepresenting the number of times observable over the year, the above equation translates to:
fQ≤|fai-faj|；
wherein f isaiFor dividing the frequency of the alias signal iajIs the frequency of the tide aliasing signal j;
correspondingly, the determining whether the aliasing period of each partial tide is divisible includes:
setting fQRe-determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite, and re-calculating the aliasing period of each partial tide and the convergence period of each partial tide aliasing signal until | fai-faj| is equal to or greater than fQTo determine the aliasing period divisible for each partial tide.
According to a second aspect of the present application, there is provided a marine satellite regression orbit determination apparatus, comprising:
the first determination unit is used for determining the minimum regression days for realizing global full coverage of satellites with different swaths according to the observation width of the satellite and the number of running turns in a revisit period;
the second determining unit is used for determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite according to the minimum regression days and the orbit parameters of the satellite;
the third determining unit is used for carrying out tidal aliasing analysis according to the partial tides of the tide and determining a tidal aliasing equation;
the first calculation unit is used for substituting the satellite orbit regression cycle into a tide aliasing equation and calculating the aliasing cycle of each tide;
the second calculation unit is used for calculating a convergence period between the chaos aliasing signals based on the aliasing period of each tide;
the judging unit is used for judging whether the aliasing period of each partial tide can be divided, if the aliasing period of each partial tide can not be divided, the second determining unit, the third determining unit, the first calculating unit and the second calculating unit are triggered to recalculate the aliasing period of each partial tide and the convergence period of the aliasing signal of each partial tide until the aliasing period of each partial tide can be divided; if the aliasing period of each tide is separable, triggering a fourth determining unit;
and the fourth determining unit is used for determining the satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number according to the operation mode of the intersection point period and the ascension intersection point right ascension precession angular velocity, and taking the determined satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number as the regression orbit design parameters of the marine satellite.
Preferably, the intersection period TNThe operation formula of (1) is as follows:
Figure BDA0002743472440000041
the rising point right ascension precession angular velocity
Figure BDA0002743472440000042
The operation formula of (1) is as follows:
Figure BDA0002743472440000051
wherein a is the distance from the satellite to the geocentric; j2 is J2 perturbation force; re6378km, earth mean radius; mu-398600.5 km3/s2I is the orbit inclination angle, and e is the orbit eccentricity.
Preferably, the first computing unit is further configured to:
for a sea surface periodic variation signal with the angular velocity sigma, the phase angle variation of a certain tide between two continuous sampling of the satellite is as follows:
Figure BDA0002743472440000052
wherein T is a satellite orbit regression period,
Figure BDA0002743472440000053
the part of tide phase change in a revisit period is less than a whole week, and n is an integer;
determination of the aliasing frequency f bya：
Figure BDA0002743472440000054
Aliasing period T of partial tideaComprises the following steps:
Figure BDA0002743472440000055
in the formula, mod represents the remainder, TaThe calculation is carried out in an interval of-180 degrees to 180 degrees.
Preferably, the second computing unit is further configured to:
convergence period T between two tidal aliasing signalsQComprises the following steps:
Figure BDA0002743472440000056
wherein, TaiFor the period of the partial tide aliasing signal i, TajFor the period of the partial tide aliasing signal j, take fa＝365/TaRepresenting the number of times observable over the year, the above equation translates to:
fQ≤|fai-faj|；
wherein the content of the first and second substances,faifor dividing the frequency of the alias signal iajIs the frequency of the tide aliasing signal j;
correspondingly, the judging unit is further configured to:
setting fQTriggering the second determining unit, the third determining unit, the first calculating unit and the second calculating unit to recalculate the aliasing period of each partial tide and the convergence period of each partial tide aliasing signal until | fai-faj| is equal to or greater than fQTo determine the aliasing period divisible for each partial tide.
According to a third aspect of the present application, there is provided a computer readable storage medium having computer instructions stored thereon, wherein the instructions, when executed by a processor, implement the steps of the method for determining a return orbit of a marine satellite.
The marine satellite regression orbit determination method and device and the storage medium provided by the embodiment of the application take the tidal aliasing problem as a consideration factor of the design of the orbit revisit cycle, can effectively avoid the situations that each tidal aliasing cycle needs to be observed for a long time and the tidal signal is inseparable, can extract tidal signals from marine observation data more quickly and conveniently by using satellite data under the condition of taking full coverage of the sea into consideration, and are more convenient to solve the harmonic parameters of the tide.
Drawings
Fig. 1 is a schematic flow chart of a method for determining a regression orbit of a marine satellite according to an embodiment of the present disclosure;
FIG. 2 is a schematic diagram of the relationship between the equator interval and the regression cycle after the regression cycle according to an embodiment of the present disclosure;
FIG. 3 is a schematic diagram of the relationship between the aliasing period and the satellite regression period for eight main partial tides according to the embodiment of the present application;
fig. 4 is a schematic structural diagram of a component of a marine satellite regression orbit determination apparatus according to an embodiment of the present application.
Detailed Description
The tide is formed by stacking a plurality of partial tides theoretically, but most partial tides have little influence, and a large number of observations and practical applications show that the eight most important taiyin and sun full-day and half-day partial tides have key influence on resolving the tides in general. The embodiment of the application carries out tide aliasing analysis on eight main tide divisions in tide, namely M2, N2, S2, K1, K2, O1, P1 and Q1, and determines a design method of a sea satellite orbit revisit cycle, and specifically comprises the following steps:
step 001: and (4) analyzing the global ocean covering capability. To achieve global tidal observation, the satellite must have the capability to cover the global sea. The satellite coverage condition is related to the satellite observation width and the number of running turns in a revisit period, and the minimum regression days for realizing global full coverage of the satellites with different swath widths can be calculated according to the corresponding relation.
Step 002: the regression period is calculated. And (3) substituting the minimum regression days in the step 001 as an input parameter into a satellite orbit equation, and adopting MATLAB to iteratively calculate the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the regression period of the satellite.
Step 003: and (4) substituting the regression cycle calculated in the step 002 into a tide aliasing equation to calculate the aliasing cycle of each partial tide.
Step 004: the convergence period of each partial tide aliasing signal calculated according to step 003.
Step 005: and (3) circularly operating the steps from 002 to 004 according to the fact that the aliasing period of each tide is divided into bases until the separability criterion is met, and operating the intersection point period and the rising intersection point right ascension precession angular velocity to enable the appropriate orbit regression period and the corresponding information such as the orbit height, the orbit intersection point period, the orbit inclination angle, the orbit operation turns and the like to be used as the relevant design parameters of the ocean satellite regression orbit.
Fig. 1 is a schematic flow chart of a method for determining a marine satellite regression orbit, which is provided in an embodiment of the present application, and as shown in fig. 1, the method for determining a marine satellite regression orbit includes the following steps:
step 01: and (4) analyzing the global ocean covering capability. Since satellites are more accessible in high latitudes, it is generally believed that full coverage in other regions can be achieved when the ground track and breadth of the satellite completely cover the equator. Therefore, when analyzing the global ocean covering capability, only the relationship between the width of the satellite swath, the number of running turns in a revisit period and the circumference of the equator needs to be analyzed, and the analysis results are shown in fig. 2 by taking the widths of 100km, 150km and 200km as examples.
Gap＝C-W×N (1)
Wherein: gap represents the red track spacing after one regression cycle, C represents the total equatorial length, W represents the swath width, and N represents the satellite running circle number in one regression cycle. And when a regression cycle is operated and the equator orbit distance is less than or equal to 0, the global ocean coverage can be realized.
Step 02: calculating a regression cycle, specifically comprising the following steps:
1. the number of satellite turns for a given regression cycle (e.g., the minimum number of regression days that can cover the world's sea) is calculated. The running circle number of the satellite is defined as a regression period multiplied by the running circle number of the satellite every day;
2. calculating the longitude difference of each circle of ground track of the satellite in operation;
3. calculating the precession speed of the right ascension at the intersection point of the tracks;
4. calculating a track intersection period;
5. calculating the height and the inclination angle of the track;
6. and calculating an accurate regression period.
The orbit in which the subsatellite point trajectories are periodically overlapped is defined as a regression orbit. Satellites traveling in such orbits will appear overhead at the same location at the same time intervals. This time interval is the regression cycle. The ocean satellite generally selects the orbit, and can observe the target area for a plurality of times to regularly obtain the change information of the target area.
Assuming that the geographic longitude of the sub-satellite points on the equator of the satellite is the same, the satellite sub-satellite point trajectories overlap everywhere. The longitude difference of the satellite after one circle of the sub-satellite geographic longitude on the equator is as follows:
Figure BDA0002743472440000081
where Δ λ is the difference in geographic longitude after one revolution; t isNIs the period of intersection; omegaeIs the rotational angular velocity of the earth;
Figure BDA0002743472440000082
the ascension angular velocity at the ascending crossing point.
If there are N, D both positive integers, then the regression condition holds, i.e.
N△λ＝2πD (3)
Thus, after D days, the sub-satellite point trajectories overlap after N satellite runs. D is the regression cycle (days).
Considering the influence of J2 perturbation on satellite orbit, the intersection period TNAnd the ascension angular velocity of the right ascension at the intersection point is:
Figure BDA0002743472440000083
Figure BDA0002743472440000091
wherein a is the distance from the satellite to the geocentric; re6378km for earth mean radius; mu-398600.5 km3/s2And (3) the gravity constant of the earth, i is the inclination angle of the orbit, and e is the eccentricity of the orbit.
The conditions met by the number of the orbits a and i can be obtained by combining the formula (3), the formula (4) and the formula (5) and performing iterative computation, and finally, an accurate regression period is computed.
Step 03: and calculating a tide splitting aliasing period.
The angular velocity is σ (frequency is
Figure BDA0002743472440000092
) For the sea surface periodic variation signal, between two consecutive sampling of the satellite, the phase angle variation of a certain tide is:
Figure BDA0002743472440000093
wherein T is the satellite orbit regression period,
Figure BDA0002743472440000094
n is an integer, and is the fraction of a revisit cycle in which the change in tidal phase is less than a full week.
The available aliasing frequencies are as follows:
Figure BDA0002743472440000095
the aliasing period is:
Figure BDA0002743472440000096
in the formula, mod represents the residue taking and the calculation result is reduced to the range of-180 degrees to 180 degrees.
Referring to fig. 3, a relationship between aliasing periods of eight main tides and a satellite regression period provided by the embodiment of the application is shown.
Step 04: the period of convergence between partial tides is calculated.
The convergence period of the two partial tides is:
Figure BDA0002743472440000097
wherein, TaiFor the period of the partial tide aliasing signal i, TajFor the period of the partial tide aliasing signal j, take fa＝365/Ta(cycle/year) represents the number of times observed a year, and equation (9) can be converted to:
fQ≤|fai-faj| (10)
wherein f isaiFor dividing the frequency of the alias signal iajIs the frequency of the tide aliasing signal j.
Step 005: setting fQValue of (A)And circularly running the steps 002 to 004 until | fai-faj| is equal to or greater than fQAnd (3) according to the formulas (4) and (5), taking the proper orbit regression period and the corresponding information such as the orbit height, the orbit intersection point period, the orbit inclination angle, the orbit running circle number and the like, and taking the determined satellite orbit regression period and the corresponding orbit height, the orbit intersection point period, the orbit inclination angle and the orbit running circle number as the design parameters of the regression orbit of the marine satellite.
Fig. 4 is a schematic structural diagram of a component of the marine satellite regression orbit determination device according to the embodiment of the present application, and as shown in fig. 4, the marine satellite regression orbit determination device according to the embodiment of the present application includes:
the first determining unit 40 is used for determining the minimum regression days for realizing global full coverage of satellites with different swaths according to the observation width of the satellites and the number of running turns in the revisit period;
the second determining unit 41 is configured to determine the orbit height, the orbit inclination, the intersection period, the number of satellite operation turns, and the satellite orbit regression period of the satellite according to the minimum regression days and the orbit parameters of the satellite;
a third determining unit 42, configured to perform a tidal aliasing analysis according to each partial tide of the tide, and determine a tidal aliasing equation;
a first calculating unit 43, configured to substitute the satellite orbit regression cycle into the tidal aliasing equation to calculate an aliasing cycle of each partial tide;
a second calculation unit 44 for calculating a convergence period between the partial tide aliasing signals based on the aliasing period of each partial tide;
a judging unit 45, configured to judge whether the aliasing period of each partial tide is divisible, if the aliasing period of each partial tide is inseparable, trigger the second determining unit 41, the third determining unit 42, the first calculating unit 43, and the second calculating unit 44 to recalculate the aliasing period of each partial tide and the convergence period of each partial tide aliasing signal until the aliasing period of each partial tide is divisible; if the aliasing period of each tide is separable, triggering a fourth determining unit;
the fourth determining unit 46 is configured to determine a satellite orbit regression period and a corresponding orbit height, an orbit intersection period, an orbit inclination angle, and an orbit running number according to an operation manner of the intersection period and the ascension angle velocity, and use the determined satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle, and orbit running number as the regression orbit design parameters of the marine satellite.
As an implementation, the intersection period TNThe operation formula of (1) is as follows:
Figure BDA0002743472440000111
the rising point right ascension precession angular velocity
Figure BDA0002743472440000112
The operation formula of (1) is as follows:
Figure BDA0002743472440000113
wherein a is the distance from the satellite to the geocentric; j2 is J2 perturbation force; re6378km, earth mean radius; mu-398600.5 km3/s2I is the orbit inclination angle, and e is the orbit eccentricity.
As an implementation manner, the first calculating unit 43 is further configured to:
for a sea surface periodic variation signal with the angular velocity sigma, the phase angle variation of a certain tide between two continuous sampling of the satellite is as follows:
Figure BDA0002743472440000114
wherein T is a satellite orbit regression period,
Figure BDA0002743472440000115
the part of tide phase change in a revisit period is less than a whole week, and n is an integer;
through the lower partEquation determining the aliasing frequency fa：
Figure BDA0002743472440000116
Aliasing period T of partial tideaComprises the following steps:
Figure BDA0002743472440000117
in the formula, mod represents the remainder, TaThe calculation is carried out in an interval of-180 degrees to 180 degrees.
As an implementation manner, the second calculating unit 44 is further configured to:
convergence period T between two tidal aliasing signalsQComprises the following steps:
Figure BDA0002743472440000118
wherein, TaiFor the period of the partial tide aliasing signal i, TajFor the period of the partial tide aliasing signal j, take fa＝365/TaRepresenting the number of times observable over the year, the above equation translates to:
fQ≤|fai-faj|；
wherein f isaiFor dividing the frequency of the alias signal iajIs the frequency of the tide aliasing signal j;
correspondingly, the determining unit 45 is further configured to:
setting fQTriggers the second determining unit 41, the third determining unit 42, the first calculating unit 43 and the second calculating unit 44 to recalculate the aliasing period of each partial tide and the convergence period of each partial tide aliasing signal until | fai-faj| is equal to or greater than fQTo determine the aliasing period divisible for each partial tide.
In the embodiment of the present disclosure, the specific manner in which each processing module and unit in the marine satellite regression orbit determination apparatus shown in fig. 4 perform operations has been described in detail in the embodiment related to the method, and will not be described in detail here.
The present invention also provides a computer readable storage medium having stored thereon computer instructions which, when executed by a processor, implement the steps of the marine satellite regression orbit determination method of the previous embodiments.
In this embodiment, the at least one processor may constitute any physical device having circuitry to perform logical operations on one or more inputs. For example, at least one processor may include one or more Integrated Circuits (ICs) including an Application Specific Integrated Circuit (ASIC), a microchip, a microcontroller, a microprocessor, all or a portion of a Central Processing Unit (CPU), a Graphics Processing Unit (GPU), a Digital Signal Processor (DSP), a Field Programmable Gate Array (FPGA), or other circuitry suitable for executing instructions or performing logical operations. The instructions executed by the at least one processor may be preloaded into a memory integrated with or embedded in the controller, for example, or may be stored in a separate memory. The memory may include Random Access Memory (RAM), Read Only Memory (ROM), hard disk, optical disk, magnetic media, flash memory, other permanent, fixed, or volatile memory, or any other mechanism capable of storing instructions. Optionally, the at least one processor may comprise more than one processor. Each processor may have a similar structure, or the processors may have different configurations that are electrically connected or disconnected from each other. For example, the processor may be a separate circuit or integrated in a single circuit. When more than one processor is used, the processors may be configured to operate independently or cooperatively. The processors may be coupled electrically, magnetically, optically, acoustically, mechanically or by other means allowing them to interact.
In the present embodiment, the non-transitory computer readable storage medium may be a ROM, a Random Access Memory (RAM), a CD-ROM, a magnetic tape, a floppy disk, an optical data storage device, and the like.
Furthermore, the features and benefits of the present invention are described with reference to exemplary embodiments. Accordingly, the invention is expressly not limited to these exemplary embodiments illustrating some possible non-limiting combination of features which may be present alone or in other combinations of features.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.

Claims (9)

1. A method for determining a return orbit of a marine satellite, the method comprising:
determining the minimum regression days for realizing global full coverage of satellites with different swaths according to the observation width of the satellites and the number of running turns in the revisiting period;
determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite according to the minimum regression days and the orbit parameters of the satellite;
carrying out tide aliasing analysis according to each partial tide of the tide, determining a tide aliasing equation, substituting the satellite orbit regression cycle into the tide aliasing equation, and calculating the aliasing cycle of each partial tide;
calculating a convergence period between the chaos aliasing signals of each partial tide based on the aliasing period of each partial tide;
judging whether the aliasing period of each partial tide can be divided, if the aliasing period of each partial tide can not be divided, re-determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite, and re-calculating the aliasing period of each partial tide and the convergence period of aliasing signals of each partial tide until the aliasing period of each partial tide can be divided;
if the aliasing period of each partial tide can be divided, determining the satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number according to the operation mode of the intersection period and the rising intersection right ascension precession angular velocity, and taking the determined satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number as the regression orbit design parameters of the marine satellite.
2. The method of claim 1, wherein the period of intersection T isNThe operation formula of (1) is as follows:
Figure FDA0002743472430000011
the rising point right ascension precession angular velocity
Figure FDA0002743472430000012
The operation formula of (1) is as follows:
Figure FDA0002743472430000013
wherein a is the distance from the satellite to the geocentric; j2 is J2 perturbation force; re6378km, earth mean radius; mu-398600.5 km3/s2I is the orbit inclination angle, and e is the orbit eccentricity.
3. The method of claim 1, wherein said calculating aliasing periods for the partial tides comprises:
for a sea surface periodic variation signal with the angular velocity sigma, the phase angle variation of a certain tide between two continuous sampling of the satellite is as follows:
Figure FDA0002743472430000021
wherein T is a satellite orbit regression period,
Figure FDA0002743472430000022
the part of tide phase change in a revisit period is less than a whole week, and n is an integer;
determination of the aliasing frequency f bya：
Figure FDA0002743472430000023
Aliasing period T of partial tideaComprises the following steps:
Figure FDA0002743472430000024
in the formula, mod represents the remainder, TaThe calculation is carried out in an interval of-180 degrees to 180 degrees.
4. The method of claim 1, wherein computing a convergence period between the partial tide aliased signals based on the aliasing periods of the partial tides comprises:
convergence period T between two tidal aliasing signalsQComprises the following steps:
Figure FDA0002743472430000025
wherein, TaiFor the period of the partial tide aliasing signal i, TajFor the period of the partial tide aliasing signal j, take fa＝365/TaRepresenting the number of times observable over the year, the above equation translates to:
fQ≤|fai-faj|；
wherein f isaiFor dividing the frequency of the alias signal iajIs the frequency of the tide aliasing signal j;
correspondingly, the determining whether the aliasing period of each partial tide is divisible includes:
setting fQRe-determining the orbital altitude, orbital inclination, intersection period, number of satellite revolutions and satellite of the satelliteThe orbit is regressed for a period, and the aliasing period of each partial tide and the convergence period of each partial tide aliasing signal are recalculated until | fai-faj| is equal to or greater than fQTo determine the aliasing period divisible for each partial tide.
5. A marine satellite regressive orbit determination apparatus, the apparatus comprising:
the first determination unit is used for determining the minimum regression days for realizing global full coverage of satellites with different swaths according to the observation width of the satellite and the number of running turns in a revisit period;
the second determining unit is used for determining the orbit height, the orbit inclination angle, the intersection point period, the satellite running circle number and the satellite orbit regression period of the satellite according to the minimum regression days and the orbit parameters of the satellite;
the third determining unit is used for carrying out tidal aliasing analysis according to the partial tides of the tide and determining a tidal aliasing equation;
the first calculation unit is used for substituting the satellite orbit regression cycle into a tide aliasing equation and calculating the aliasing cycle of each tide;
the second calculation unit is used for calculating a convergence period between the chaos aliasing signals based on the aliasing period of each tide;
the judging unit is used for judging whether the aliasing period of each partial tide can be divided, if the aliasing period of each partial tide can not be divided, the second determining unit, the third determining unit, the first calculating unit and the second calculating unit are triggered to recalculate the aliasing period of each partial tide and the convergence period of the aliasing signal of each partial tide until the aliasing period of each partial tide can be divided; if the aliasing period of each tide is separable, triggering a fourth determining unit;
and the fourth determining unit is used for determining the satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number according to the operation mode of the intersection point period and the ascension intersection point right ascension precession angular velocity, and taking the determined satellite orbit regression period and the corresponding orbit height, orbit intersection period, orbit inclination angle and orbit running circle number as the regression orbit design parameters of the marine satellite.
6. The apparatus of claim 5, wherein the intersection period T isNThe operation formula of (1) is as follows:
Figure FDA0002743472430000031
the rising point right ascension precession angular velocity
Figure FDA0002743472430000032
The operation formula of (1) is as follows:
Figure FDA0002743472430000033
wherein a is the distance from the satellite to the geocentric; j2 is J2 perturbation force; re6378km, earth mean radius; mu-398600.5 km3/s2I is the orbit inclination angle, and e is the orbit eccentricity.
7. The apparatus of claim 5, wherein the first computing unit is further configured to:
for a sea surface periodic variation signal with the angular velocity sigma, the phase angle variation of a certain tide between two continuous sampling of the satellite is as follows:
Figure FDA0002743472430000041
wherein T is a satellite orbit regression period,
Figure FDA0002743472430000042
the part of tide phase change in a revisit period is less than a whole week, and n is an integer;
determination of the aliasing frequency f bya：
Figure FDA0002743472430000043
Aliasing period T of partial tideaComprises the following steps:
Figure FDA0002743472430000044
in the formula, mod represents the remainder, TaThe calculation is carried out in an interval of-180 degrees to 180 degrees.
8. The method of claim 1, wherein the second computing unit is further configured to:
convergence period T between two tidal aliasing signalsQComprises the following steps:
Figure FDA0002743472430000045
wherein, TaiFor the period of the partial tide aliasing signal i, TajFor the period of the partial tide aliasing signal j, take fa＝365/TaRepresenting the number of times observable over the year, the above equation translates to:
fQ≤|fai-faj|；
wherein f isaiFor dividing the frequency of the alias signal iajIs the frequency of the tide aliasing signal j;
correspondingly, the judging unit is further configured to:
setting fQTriggering the second determining unit, the third determining unit, the first calculating unit and the second calculating unit to recalculate the aliasing period of each partial tide and the convergence period of each partial tide aliasing signal until | fai-faj| is equal to or greater than fQTo determine the aliasing period divisible for each partial tide.
9. A computer readable storage medium having computer instructions stored thereon, wherein the instructions, when executed by a processor, perform the steps of the marine satellite regression orbit determination method according to any one of claims 1 to 4.
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