CN109323698B - Space target merle multi-model tracking and guiding method - Google Patents
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Abstract
The invention discloses a space target meteor fall multiple model tracking and guiding method, which comprises the steps of analyzing the meteor fall forecast principle of a space target, comprehensively using a plurality of atmosphere models, solving an atmosphere resistance coefficient CD by combining a tracking arc section of a measuring station, correcting the atmosphere resistance coefficient CD by combining radar measurement data and calculating the meteor fall forecast, is scientific and reasonable, is safe and convenient to use, combines the track dynamics characteristics of the meteor fall target and the adaptive range of different atmosphere models, adopts the methods of atmosphere model switching and damping factor discrete solution to carry out meteor fall forecast, improves the accuracy of the meteor fall forecast, can adapt to the settlement and forecast of an ultra-low track, estimates the CD value by combining the tracking arc section, ensures that the discrete change of the meteor fall is in line with the change trend of actually measured atmosphere as much as possible, comprehensively uses a plurality of atmosphere models in the rapid guiding process, carries out model replacement along with the change of height, and reducing the spatial target meteor forecast error to be within 10 percent.
Description
Technical Field
The invention relates to the technical field of measurement and control management of an orbital spacecraft, in particular to a space target merle multi-model tracking and guiding method.
Background
Since the 1957 that human beings enter the space, about 7000 spacecrafts enter the space, wherein more than six hundred satellites naturally fall out, space activities generate fragments with the size of more than hundreds of thousands of centimeters, more and more incidents of the falling out of the space exist, in order to reduce the loss generated by the falling out of the space, the falling out forecast needs to be accurate as much as possible, but the accuracy of the falling out of the space at present hardly meets the requirement of ground personnel on property risk avoidance, and the main reasons for generating errors are that the dynamic model error of the space craft and the observation data for acquiring the falling out target before the falling out of the space are small in quantity and poor in quality;
due to the action of atmospheric resistance, the energy of a satellite running along an elliptical orbit is continuously dissipated, the flying height is continuously reduced, and particularly the far place is more quickly reduced, so that the orbit gradually tends to be circular along with the increase of time, the orbit height is further reduced, the atmospheric density is rapidly increased below the ground height of 110km, the satellite orbit bends downwards steeply and is almost vertically entered into a dense atmosphere, and finally the satellite is quickly burnt or falls on the earth, and the satellite meteority forecast is to calculate the meteority time and the meteority place of the satellite;
the satellite meteority forecast can be directly integrated to the landing moment through a numerical integration method, the service life and the meteority place of the satellite can also be given, but the change of the atmospheric density is complex, and the posture in the satellite motion is not determined, so that the accurate calculation of the orbit service life and the meteority place is difficult;
in addition, because the current atmospheric density models have different application ranges and have respective errors, for example, for a low-orbit satellite of 300 kilometers, only the error of the atmospheric perturbation model is assumed to be 5%, the orbit calculation error of the satellite in 24 hours reaches the magnitude of several kilometers, and even if other various perturbation forces are completely ignored, the influence of the orbit calculation error on the accuracy of the orbit is only within the magnitude of tens of meters, so that different atmospheric density models are urgently needed to be adopted for different heights when meteor fall tracking and guiding are performed on a target, and therefore, a novel space target meteor fall multi-model tracking and guiding method is urgently needed to solve the problems.
Disclosure of Invention
The invention provides a space target merle multiple model tracking and guiding method, which can effectively solve the problems that the satellite merle forecast provided in the background technology can be directly integrated to the landing moment through a numerical integration method, the service life and the merle place of a satellite can also be provided, but the accurate calculation of the orbit service life and the merle place is difficult because the atmospheric density change is complex and the posture in the satellite motion is uncertain, and the existing atmospheric density models have different application ranges and have respective errors.
In order to achieve the purpose, the invention provides the following technical scheme: a space target merle multi-model tracking and guiding method comprises the following steps:
s1, analyzing the space target meteor forecast principle;
s2, comprehensively using a plurality of atmosphere models;
s3, tracking the arc-segment solution atmospheric resistance coefficient CD by combining a measuring station;
s4, correcting the atmospheric drag coefficient CD by combining radar measurement data;
and S5, calculating meteor forecast.
According to the above technical solution, in the step S1, at the end of the life of the low-orbit satellite, the low-orbit satellite will enter the atmosphere again, the accuracy of meteor prediction is mainly affected by the atmosphere, and the change of the spatial atmospheric density is mainly affected by the sun' S10.7 cm radiation flow F10.7And the influence of two space environment parameters of the geomagnetic index Ap, in orbit calculation, a plurality of atmospheric resistance coefficients CD change rates are calculated according to the tracking of a measuring station, so that the solar radiation flow F can be obviously weakened10.7The influence of the error of the parameter value on orbit determination and prediction can be realized, meanwhile, the attitude analysis and the flight state judgment can be carried out on the meteor satellite by utilizing the radar measurement data, the atmospheric resistance coefficient CD is corrected, and the meteor prediction precision is improved.
According to the above technical solution, in step S2, for the high-rise atmosphere above 200km, it is actually a thin atmosphere, for the spacecraft whose size is not particularly large, the motion is in the free molecular flow, and the high mach number spacecraft flies in the thin atmosphere in this state, the aerodynamic force applied to the spacecraft mainly represents a resistance, and has a good approximate expression:
V＝v-va
wherein v and vaEach satellite and atmosphere relative geocentricA velocity vector of a coordinate system;
for a classical effective face value ratio of 109If the altitude is above 300km, the atmospheric drag perturbation is not higher than 10-6Namely, for the motion of the medium and low orbit satellites, the perturbation magnitude of the atmospheric resistance can be treated as a second order small quantity;
according to the characteristics of the atmosphere model, different atmosphere models are comprehensively used at different orbit heights, and the method comprises the following steps:
(1) the height of the orbit is more than 120 kilometers, and an MSIS-90 model and a DTM94 model are used on average;
(2) the height of the track is more than 90 kilometers and less than 120 kilometers, and the Jacchia-77 model and the improved Harris-Priester model are used on average;
(3) the orbit height is less than 90 kilometers, and a ballistic integration method is adopted.
According to the technical scheme, the atmospheric temperature, components and density in the MSIS-90 mode from the ground to the hot layer interval take the influence of atmospheric component distribution into consideration, the atmospheric temperature, components and density distribution is compiled into a mode with wider time and space coverage by using the neutral gas components measured by an on-satellite mass spectrometer and the temperature data measured by an incoherent scattering radar, and the atmospheric temperature, atmospheric components and content observation data measured by a plurality of rockets, satellites and the incoherent scattering radar on the ground, fitting the model on the basis of a semi-empirical formula, wherein the atmospheric mode describes geomagnetic variation by using a 3-hour Ap geomagnetic variable, to highlight the instability of the thermal ionosphere, the DTM model is a three-dimensional thermal atmosphere model represented by spherical harmonics, the model is suitable for calculating the atmospheric density at the height of 120km or more, and a model of Jacchia semi-empirical formula and an assumption of diffusion balance are applied when the model is established, and satellite orbit data of about 20 years are used.
According to the technical scheme, the Jacchia-71 atmospheric model uses a fixed boundary condition with the height of 90km as the lower limit, a numerical integration method is used for solving corresponding differential equations in each atmosphere, another asymptotic function is selected for the temperature distribution of the atmosphere above 125km to obtain the integrable form of the diffusion differential equation, the Jacchia-71 atmospheric model is suitable for calculating the atmospheric density at the height higher than 125km, and after the Jacchia-71 atmospheric model is established, a satellite is used for calculating the temperature distribution of the atmosphere above 125km, and the integrable form of the diffusion differential equation is obtainedThe Jacchia-77 atmosphere model is formed by taking the newly found atmosphere change rules into consideration and performing supplementary modification on the basis of the Jacchia-71 atmosphere model, the basic method is the same as that of the Jacchia-71 atmosphere model, the Jacchia-77 atmosphere model is suitable for calculating the atmosphere density at the position with the height of more than 90km, and the improved Harris-Priester model is based on different sun 10.7 cm radiation flow F10.7The maximum value and the minimum value of the daily change of the atmospheric density at each altitude are provided by different table values, the daily change correction is performed by using the maximum value and the minimum value of the atmospheric density, and the model is suitable for calculating the atmospheric density at the altitude of more than 100 km.
According to the above technical solution, in the step S3, in a general orbit determination method, only one atmospheric resistance coefficient CD is estimated in a full arc, which generally can only absorb an average part of an atmospheric density calculation error, but an error caused by a rapid fluctuation part of the atmospheric density is hard to absorb, especially when the activity of the sun and the geomagnetic index is severe, a plurality of atmospheric resistance factors absorb an error of atmospheric resistance perturbation calculation, for an orbit determination arc for 2 days, a plurality of atmospheric damping factors can be solved, one atmospheric resistance coefficient CD at the start time and one atmospheric resistance coefficient CD at the end time of the orbit determination arc, a plurality of atmospheric resistance coefficients CD are set in the middle of the orbit determination arc in combination with a measuring station, and the atmospheric resistance coefficients CD values at other arbitrary times can be obtained by interpolation of two points;
the atmospheric resistance coefficient CD corresponding to any other time is expressed by the following formula:
the CDs given by the segmentation method are still continuous, the geomagnetic index fluctuation with the change period larger than 12 hours can be well absorbed, and the number of the estimated atmospheric resistance coefficients CD can be correspondingly reduced and increased for data arcs with different lengths and geomagnetic index fluctuation which needs to reflect higher frequencies.
According to the technical scheme, in the step S4, because the radar is not influenced by weather, the radar can track the visible arc, the attitude parameters of the meteorite target can be inverted by utilizing radar broadband image data, so that the flight state of the target is judged, if the target is in a disintegration state, the meteorite target can be ablated in the atmosphere during the meteorite process, and if the target is in a normal flight attitude, the atmospheric damping coefficient is subjected to experience correction by combining radar narrow-band RCS data, so that the meteorite forecasting precision is improved.
According to the above technical solution, in the step S5,
(1) calculating the time length of satellite falling and the change of the orbit height along with the time according to a satellite orbit life calculation method;
(2) if the height of the track is more than 120 kilometers, averagely using an MSIS-90 model and a DTM94 model, solving two atmospheric resistance coefficients CD at the initial position of the fixed track arc section, and simultaneously carrying out empirical correction on the atmospheric resistance coefficients CD by using radar measurement data;
(3) if the track height is larger than 90 kilometers and smaller than 120 kilometers, averagely using a Jacchia-77 model and an improved Harris-Priester model, solving two atmospheric resistance coefficients CD at the initial position of the orbit determination arc section, and simultaneously carrying out empirical correction on the atmospheric resistance coefficients CD by using radar measurement data;
(4) if the orbit height is less than 90 kilometers, calculating the position and time of the satellite falling by adopting a ballistic integral method.
According to the technical scheme, the method for estimating the satellite orbit life comprises the following steps:
is provided with
The track life L is then:
where n is the satellite mean motion angular velocity in circles/d2；
a is the semi-major axis of the track, and the unit is km;
e-track eccentricity;
h, large air density elevation at a close place, wherein the unit is km;
mu-the rate of change of the atmospheric density elevation, which can be generally 0.1;
I0,I1-a bessel function;
j is an empirical number, and gradually decreases in size from 1 to 0.2, depending on z, where J equals 1, z equals 0, J equals 0.2, z equals 1.2, and J is negligible when z > 1.2,
the invention has the beneficial effects that: the method is scientific and reasonable, is safe and convenient to use, combines the orbit dynamics characteristics of meteor objects and the adaptation ranges of different atmospheric models, adopts the methods of atmospheric model switching and damping factor discrete solution to forecast meteor objects, improves the accuracy of meteor object forecast, can adapt to settlement and forecast of ultra-low orbits, combines a tracking arc section to estimate the CD value of the atmospheric resistance coefficient, the discrete change of the atmospheric resistance coefficient accords with the change trend of the actually measured atmosphere as much as possible, comprehensively uses a plurality of atmospheric models in the rapid guiding process, carries out model replacement along with the change of height, improves the accuracy of the computation of the meteor object forecast of the space target, and reduces the meteor object forecast error of the space target to be within 10 percent by the method.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic diagram of the trace-and-guide steps of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.
Example (b): as shown in FIG. 1, the invention provides a technical solution, a space target merle multi-model tracking and guiding method, comprising the following steps:
s1, analyzing the space target meteor forecast principle;
s2, comprehensively using a plurality of atmosphere models;
s3, tracking the arc-segment solution atmospheric resistance coefficient CD by combining a measuring station;
s4, correcting the atmospheric drag coefficient CD by combining radar measurement data;
and S5, calculating meteor forecast.
According to the technical scheme, in the step S1, at the end of the life of the low-orbit satellite, the low-orbit satellite enters the atmosphere again, the accuracy of meteor forecast is mainly influenced by the atmosphere, and the change of the space atmospheric density is mainly influenced by the 10.7 cm radiation flow F of the sun10.7And the influence of two space environment parameters of the geomagnetic index Ap, in orbit calculation, the change rate of a plurality of atmospheric resistance coefficients CD is calculated according to the tracking of a measuring station, so that the solar radiation flow F can be obviously weakened10.7The error of the parameter value has influence on orbit determination and prediction, and meanwhile, the attitude analysis and flight state judgment can be carried out on the meteor satellite by utilizing the radar measurement data, the atmospheric resistance coefficient is corrected, and the meteor prediction precision is improved.
According to the technical scheme, in step S2, for the high-rise atmosphere above 200km, the high-rise atmosphere is actually a thin atmosphere, for the spacecraft with a not particularly large scale, the motion of the spacecraft is in a free molecular flow, and the high-mach number spacecraft flies in the thin atmosphere in this state, the aerodynamic force applied to the spacecraft mainly represents a resistance and has a good approximate expression:
V＝v-va
wherein v and vaEach is a velocity vector of the satellite and the atmosphere relative to a geocentric coordinate system;
for a classical effective face value ratio of 109If the altitude is above 300km, the atmospheric drag perturbation is not higher than 10-6Namely, for the motion of the medium and low orbit satellites, the perturbation magnitude of the atmospheric resistance can be treated as a second order small quantity;
according to the characteristics of the atmosphere model, different atmosphere models are comprehensively used at different orbit heights, and the method comprises the following steps:
(1) the height of the orbit is more than 120 kilometers, and an MSIS-90 model and a DTM94 model are used on average;
(2) the height of the track is more than 90 kilometers and less than 120 kilometers, and the Jacchia-77 model and the improved Harris-Priester model are used on average;
(3) the orbit height is less than 90 kilometers, and a ballistic integration method is adopted.
According to the technical scheme, the atmospheric temperature, components and density in the MSIS-90 mode from the ground to the hot layer interval take the influence of atmospheric component distribution into consideration, the atmospheric temperature, components and density distribution is compiled into a mode with wider time and space coverage by using the neutral gas components measured by an on-satellite mass spectrometer and the temperature data measured by an incoherent scattering radar, and the atmospheric temperature, atmospheric components and content observation data measured by a plurality of rockets, satellites and the incoherent scattering radar on the ground, fitting the model on the basis of a semi-empirical formula, wherein the atmospheric mode describes geomagnetic variation by using a 3-hour Ap geomagnetic variable, to highlight the instability of the thermal ionosphere, the DTM model is a three-dimensional thermal atmosphere model represented by spherical harmonics, the model is suitable for calculating the atmospheric density at the height of 120km or more, and a model of Jacchia semi-empirical formula and an assumption of diffusion balance are applied when the model is established, and satellite orbit data of about 20 years are used.
According to the technical scheme, the Jacchia-71 atmosphere modelSolving corresponding differential equations in each atmosphere by a numerical integration method under a fixed boundary condition with the height of 90km as a lower limit, another asymptotic function is selected for the temperature distribution of the atmosphere with the height of more than 125km to obtain the integrable form of a diffusion differential equation, the method is suitable for calculating the atmospheric density at the position with the height of more than 125km, after the Jacchia-71 atmospheric model is established, the high-rise atmosphere is directly measured by using a satellite-borne instrument, certain new laws of high-rise atmosphere change are revealed, and after the Jacchia-77 atmosphere model considers the newly discovered laws of atmosphere change, is formed by making supplementary modification on the basis of a Jacchia-71 atmosphere model, the basic method is the same as that of a Jacchia-71 atmosphere model, the Jacchia-77 atmosphere model is suitable for calculation of the atmosphere density at the height of more than 90km, and the improved Harris-Priester model is based on different sun 10.7 cm radiation flow F.10.7The maximum value and the minimum value of the daily change of the atmospheric density at each altitude are provided by different table values, the daily change correction is performed by using the maximum value and the minimum value of the atmospheric density, and the model is suitable for calculating the atmospheric density at the altitude of more than 100 km.
According to the technical scheme, in the step S3, in a general orbit determination method, only one atmospheric resistance coefficient CD is estimated in a full arc section, which generally can only absorb an average part of an atmospheric density calculation error, but an error caused by a rapid fluctuation part of the atmospheric density is difficult to absorb, especially when the activity of the sun and the geomagnetic index is severe, a plurality of atmospheric resistance factors absorb the atmospheric resistance perturbation calculation error, for an orbit determination arc section for 2 days, a plurality of atmospheric damping factors can be solved, one atmospheric resistance coefficient CD at the starting time and one atmospheric resistance coefficient CD at the ending time of the orbit determination arc section, a plurality of atmospheric resistance coefficients CD are set in the middle of the orbit determination arc section in combination with a measuring station, and the atmospheric resistance coefficient CD values at any other time can be obtained by two-point interpolation;
the atmospheric resistance coefficient CD corresponding to any other time is expressed by the following formula:
the atmospheric resistance coefficient CD given by the segmentation method is still continuous, the geomagnetic index fluctuation with the change period larger than 12 hours can be well absorbed, and the number of the estimated atmospheric resistance coefficients CD can be correspondingly reduced and increased for data arc segments with different lengths and geomagnetic index fluctuation which needs to reflect higher frequencies.
According to the technical scheme, in the step S4, as the radar is not influenced by weather, the visible arc can be tracked, the attitude parameters of the meteorite target can be inverted by utilizing radar broadband image data, so that the flight state of the target is judged, if the target is in a disintegration state, the meteorite target can be ablated in the atmosphere during the meteorite process, and if the target is in a normal flight attitude, the atmospheric damping coefficient is subjected to experience correction by combining radar narrow-band RCS data, so that the meteorite forecasting precision is improved.
According to the above technical solution, in step S5,
(1) calculating the time length of satellite falling and the change of the orbit height along with the time according to a satellite orbit life calculation method;
(2) if the height of the track is more than 120 kilometers, averagely using an MSIS-90 model and a DTM94 model, solving two atmospheric resistance coefficients CD at the initial position of the fixed track arc section, and simultaneously carrying out empirical correction on the atmospheric resistance coefficients CD by using radar measurement data;
(3) if the track height is larger than 90 kilometers and smaller than 120 kilometers, averagely using a Jacchia-77 model and an improved Harris-Priester model, solving two atmospheric resistance coefficients CD at the initial position of the orbit determination arc section, and simultaneously carrying out empirical correction on the atmospheric resistance coefficients CD by using radar measurement data;
(4) if the orbit height is less than 90 kilometers, calculating the position and time of the satellite falling by adopting a ballistic integral method.
According to the technical scheme, the method for estimating the satellite orbit life comprises the following steps:
is provided with
The track life L is then:
where n is the satellite mean motion angular velocity in circles/d2；
a is the semi-major axis of the track, and the unit is km;
e-track eccentricity;
h, large air density elevation at a close place, wherein the unit is km;
mu-the rate of change of the atmospheric density elevation, which can be generally 0.1;
I0,I1-a bessel function;
j is an empirical number, and gradually decreases in size from 1 to 0.2, depending on z, where J equals 1, z equals 0, J equals 0.2, z equals 1.2, and J is negligible when z > 1.2,
based on the above, the invention has the advantages that: the method is scientific and reasonable, is safe and convenient to use, combines the orbit dynamics characteristics of meteor objects and the adaptation ranges of different atmospheric models, adopts the methods of atmospheric model switching and damping factor discrete solution to forecast meteor objects, improves the accuracy of meteor object forecast, can adapt to settlement and forecast of ultra-low orbits, combines a tracking arc section to estimate the CD value of the atmospheric resistance coefficient, the discrete change of the atmospheric resistance coefficient accords with the change trend of the actually measured atmosphere as much as possible, comprehensively uses a plurality of atmospheric models in the rapid guiding process, carries out model replacement along with the change of height, improves the accuracy of the computation of the meteor object forecast of the space target, and reduces the meteor object forecast error of the space target to be within 10 percent by the method.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A space target merle multi-model tracking and guiding method is characterized by comprising the following steps:
s1, analyzing the space target meteor forecast principle;
s2, comprehensively using a plurality of atmosphere models;
s3, tracking the arc-segment solution atmospheric resistance coefficient CD by combining a measuring station;
s4, correcting the atmospheric drag coefficient CD by combining radar measurement data;
s5, calculating meteor forecast;
in the step S5, in the step S,
(1) calculating the time length of satellite falling and the change of the orbit height along with the time according to a satellite orbit life calculation method;
(2) if the height of the track is more than 120 kilometers, averagely using an MSIS-90 model and a DTM94 model, solving two atmospheric resistance coefficients CD at the initial position of the fixed track arc section, and simultaneously carrying out empirical correction on the atmospheric resistance coefficients CD by using radar measurement data;
(3) if the track height is larger than 90 kilometers and smaller than 120 kilometers, averagely using a Jacchia-77 model and an improved Harris-Priester model, solving two atmospheric resistance coefficients CD at the initial position of the orbit determination arc section, and simultaneously carrying out empirical correction on the atmospheric resistance coefficients CD by using radar measurement data;
(4) if the orbit height is less than 90 kilometers, calculating the location and time of the satellite falling by adopting a ballistic integral method;
the method for estimating the satellite orbit life is as follows:
is provided with
The track life L is then:
where n is the satellite mean motion angular velocity in circles/d2；
a is the semi-major axis of the track, and the unit is km;
e-track eccentricity;
h, large air density elevation at a close place, wherein the unit is km;
mu is the change rate of the atmospheric density elevation, and is taken as 0.1;
I0,I1-a bessel function;
j is an empirical number, and decreases gradually from 1 to 0.2, depending on z, where J equals 1, z equals 0, J equals 0.2, z equals 1.2, and J is ignored when z > 1.2,
2. the method for tracking and guiding the space target merle multiple model according to claim 1, characterized in that: at the end of the life of the low-orbit satellite in the step S1The low orbit satellite will enter the atmosphere again, the accuracy of meteor forecast is mainly influenced by the atmosphere, the change of space atmosphere density is mainly influenced by the sun's 10.7 cm radiation flow F10.7And the influence of two space environment parameters of the geomagnetic index Ap, in orbit calculation, the change rate of a plurality of atmospheric resistance coefficients CD is calculated according to the tracking of a measuring station, and the solar radiation flow F is obviously weakened10.7The error of the parameter value has influence on orbit determination and prediction, and meanwhile, the radar measurement data is utilized to perform attitude analysis and flight state judgment on the meteor satellite, so that the atmospheric resistance coefficient CD is corrected, and the meteor prediction precision is improved.
3. The method for tracking and guiding the space target merle multiple model according to claim 1, characterized in that: in the step S3, in the orbit determination method, the full arc segment only estimates one atmospheric resistance coefficient CD, which can only absorb the average part of the atmospheric density calculation error, but the error caused by the rapid fluctuation part of the atmospheric density is difficult to absorb, when the sun and the geomagnetic index activity are severe, the atmospheric resistance coefficients CD absorb the atmospheric resistance perturbation calculation error, for the 2-day orbit determination arc segment, the atmospheric resistance coefficients CD are solved, one atmospheric resistance coefficient CD at the start time of the orbit determination arc segment and one atmospheric resistance coefficient CD at the end time, the atmospheric resistance coefficients CD are set in the middle in combination with the tracking arc segment of the measuring station, and the atmospheric resistance coefficient CD values at other arbitrary times are obtained by two-point interpolation;
the atmospheric resistance coefficient CD corresponding to any other time is expressed by the following formula:
the atmospheric resistance coefficient CD given by the segmentation method is still continuous, the geomagnetic index fluctuation with the change period larger than 12 hours is well absorbed, and for data arcs with different lengths and geomagnetic index fluctuation needing to reflect higher frequency, the number of the estimated atmospheric resistance coefficients CD is correspondingly reduced and increased.
4. The method for tracking and guiding the space target merle multiple model according to claim 1, characterized in that: in the step S4, because the radar is not affected by weather, the radar can track the visible arc, and the attitude parameters of the meteorite target are inverted by using the radar broadband image data, so that the flight state of the target is judged, if the target is in the disintegration state, the meteorite can be ablated in the atmosphere during the meteorite process, and if the target is in the normal flight attitude, the atmospheric drag coefficient CD is subjected to experience correction by combining with the radar narrow-band RCS data, so that the meteorite forecasting precision is improved.
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| CN111259310B (en) * | 2020-01-14 | 2023-05-12 | 中国科学院国家空间科学中心 | Thermal layer atmospheric density prediction method and system based on distributed sensing units |
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