CN113359159B - Multi-satellite positioning and orbit determination precision rapid analysis method for space-based space target monitoring - Google Patents
Multi-satellite positioning and orbit determination precision rapid analysis method for space-based space target monitoring Download PDFInfo
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Abstract
The invention discloses a multi-satellite positioning orbit determination precision rapid analysis method for space-based space target monitoring, and relates to the technical field of space target monitoring. The method firstly quickly analyzes the multi-satellite positioning error according to the single-station data type, the measurement error and the multi-satellite geometric configuration, and then gives the relation between the semi-major axis error of short arc section orbit determination and the positioning error by utilizing the track propagation characteristic. The method can be suitable for the design of a multi-satellite positioning and orbit determination system for space-based space target monitoring, can also be popularized and applied to the design of a multi-satellite \ multi-station combined positioning and orbit determination system for space-based space, can quickly and quantitatively evaluate the space target positioning and orbit determination results under different constellation designs, has clear principle, simple calculation and accurate evaluation, and can be widely applied to space-based space target monitoring systems.
Description
Technical Field
The invention relates to the technical field of space target monitoring, in particular to a multi-satellite positioning orbit determination precision rapid analysis method for space-based space target monitoring.
Background
Space-based space target monitoring is an important development direction in the field of space target monitoring, and has the advantages of high detection frequency, good observation conditions and the like which are not possessed by more foundation detection. The space-based space target monitoring satellite can theoretically carry various types of detection loads such as radar, optical and passive reconnaissance, and the like, and because the miniaturization of the remote monitoring radar is not mature, the monitoring satellite is mostly an optical monitoring satellite and a passive reconnaissance satellite in practice. Unlike radar detection, optical monitoring satellites and passive receiving satellites can only acquire angle measurement information, cannot acquire ranging information, cannot acquire a target position through single measurement, and have high difficulty in executing real-time target indication and high-precision short arc orbit determination tasks.
According to the requirements of real-time target indication and orbit determination forecasting, a set of space-based real-time space target monitoring means based on multiple satellites and multiple stations is provided, positioning and orbit determination accuracy can be rapidly analyzed and evaluated, the method is a necessary basis of space-based space target monitoring overall design, and has important significance for development of multi-satellite networking monitoring technology for space-based space target monitoring.
Disclosure of Invention
In view of the above, the invention provides a method for rapidly analyzing multi-satellite positioning and orbit determination precision of space-based space target monitoring, which can rapidly analyze multi-satellite positioning and orbit determination precision of space-based space target monitoring, can rapidly and quantitatively evaluate space target positioning and orbit determination results under different constellation designs, has clear principle, simple calculation and accurate evaluation, and can be widely applied to a space-based space target monitoring system.
In order to achieve the purpose, the technical scheme of the invention is as follows:
and analyzing to obtain a multi-satellite positioning error delta X according to the geometric configuration and the measurement error of the satellite and by combining the types of the satellite sight line cross positioning and the time difference positioning.
Using the observation arc duration, the target orbit and the multi-satellite positioning error DeltaX, using the formula
And calculating the semimajor axis error delta a of the short arc orbit determination, and effectively evaluating the multi-satellite positioning orbit determination efficiency, wherein mu is an earth gravity constant, a is an approximate semimajor axis of the target orbit, and delta T is observation time.
Further, according to the geometric configuration and the measurement error of the satellite, the multi-satellite positioning error delta X is obtained through analysis by combining the satellite sight line cross positioning and the time difference positioning types, and specifically:
if the satellite sight line cross positioning is double-star sight line cross positioning, the angle measurement error of the pitch angle and the azimuth angle of a single star is delta alpha, the distance interval of double stars is L, and the vertical distance difference between a target and a double-star connecting line is R, then the obtained double stars are obtainedThe positioning error Δ X of the star is: Δ X ═ 2R 2 Δα/L。
Furthermore, the adopted double-star sight line cross positioning adopts two 800-kilometer sun synchronous orbit monitoring satellites to observe the geosynchronous orbit at 42165 kilometers in a smooth manner, and the observation precision is 5 arc seconds.
Further, according to the geometric configuration and the measurement error of the satellite, the multi-satellite positioning error delta X is obtained through analysis by combining the satellite sight line cross positioning and the time difference positioning types, and specifically:
if the satellite sight line cross positioning is the three-satellite radio time difference positioning, the three-satellite middle edge satellite and the middle satellite form two time difference positioning systems, the time difference measurement error of the single time difference positioning system is delta t, the distance interval between the two positioning systems is L, the vertical distance difference of a target from a connecting line of the two positioning systems is R, and the obtained positioning error delta X of the multiple satellites is delta X which is 2R 2 CΔt/L 2 Wherein the speed of light C is 3 × 10 8 m/s。
Furthermore, when the three-satellite radio time difference positioning is carried out, three radio detection satellites of the earth synchronous belt are adopted to form two groups of time difference positioning systems, the time difference measurement precision delta t is 600 nanoseconds, the phase difference between the two groups of systems is 15 degrees, the equivalent distance interval is 11039 kilometers, the time difference cross positioning is carried out on the low-orbit solar synchronous satellite, and the vertical distance is about 42165 kilometers.
Has the advantages that:
1. the invention relates to a multi-satellite positioning and orbit determination precision rapid analysis method for space-based space target monitoring. The method can be suitable for the design of a multi-satellite positioning and orbit determination system for space-based space target monitoring, can also be popularized and applied to the design of a multi-satellite \ multi-station combined positioning and orbit determination system for space-based space, can quickly and quantitatively evaluate the space target positioning and orbit determination results under different constellation designs, has clear principle, simple calculation and accurate evaluation, and can be widely applied to space-based space target monitoring systems.
2. The invention simultaneously provides the initial design of the multi-satellite real-time positioning orbit determination system, provides a typical error approximate calculation method for double-satellite cross positioning and three-satellite time difference positioning by using the geometrical configurations of constellations and targets, and can be popularized and applied to the analysis of the multi-satellite positioning system.
3. According to the propagation principle of the semimajor axis and the trackside errors of the track, the invention deduces the relation between the semimajor axis errors and the multi-star positioning errors of the short arc orbit determination, can quickly analyze the short arc orbit determination precision and support the efficiency evaluation of a space-based space target monitoring system.
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Fig. 1 is a flowchart of a multi-satellite positioning and orbit determination precision rapid analysis method for space-based space target monitoring according to an embodiment of the present invention.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a multi-satellite positioning orbit determination precision rapid analysis method for space-based space target monitoring. The method has the core that joint positioning and orbit determination are carried out by utilizing multi-satellite angle measurement information, real-time target position determination is carried out, a basic cross positioning error calculation method is given for two measurement modes of sight cross positioning and time difference positioning and a simple cross positioning principle, and on the basis, a semi-long axis orbit determination error of a short arc track is analyzed by utilizing a track tracing error propagation theory, so that positioning and orbit determination efficiency after multi-satellite fusion measurement is rapidly determined.
The implementation scheme of the invention mainly comprises two parts of space-based cross positioning precision rapid analysis and space-based short arc orbit determination precision rapid analysis.
Space-based cross positioning precision rapid analysis method
For a single space-based optical monitoring satellite and a space-based radio detection satellite, only angle measurement data can be obtained, single-station real-time positioning and short arc orbit determination cannot be realized, and the monitoring efficiency of the satellite is greatly restricted. In order to obtain high-frequency monitoring data and large monitoring airspace, the monitoring satellites all adopt a plurality of marshalling satellites to perform tasks, and generally, the monitoring targets of the satellites are different. However, in order to obtain the real-time position and the short-time high-precision orbit of the key target, it is necessary to provide a working mode of multi-satellite combined observation of the same target to develop real-time cross positioning. The multi-satellite combined observation has fewer opportunities, the time for developing task planning is short, how to quickly evaluate the multi-satellite positioning and orbit determination precision can effectively support the design of the orbit position of the constellation and the effective task planning, and the method is of great importance to the expansion of a space-based space target monitoring mode.
The method mainly analyzes two scenes of double-star sight line cross positioning and three-star radio time difference positioning, and can be easily popularized to multi-star or space-ground combined positioning scenes.
For double-satellite positioning, assuming that angular measurement errors such as a pitch angle and an azimuth angle of a single satellite are delta alpha, a distance interval of the double satellites is L, and a vertical distance difference between a target and a connecting line of the double satellites is R, an equivalent position error of the single-satellite measurement is approximately R delta alpha through calculation, and according to geometrical configurations of the double satellites and the target, a positioning error delta X of the double satellites is approximately obtained
ΔX＝2R 2 Δα/L (1)
Although an approximate calculation, the method can be basically used as a quantitative basis for the overall design in the aspect of evaluating the accuracy of the positioning precision magnitude of the constellation. For example, two 800 km solar synchronous orbit monitoring satellites observe a geosynchronous orbit at 42165 km with a light observation precision of 5 arc seconds, and the distance between the two satellites is about 10151 km and 14356 km under the assumption that the phase difference of the two satellites is respectively 90 degrees and 180 degrees, and the positioning errors of the two satellites are respectively 8.5 km and 6 km through quick calculation by using the formula (1).
For the three-star radio time difference positioning, suppose that the middle edge satellite and the middle satellite of the three-star form two time difference positioning systems, the time difference measurement error of the single time difference positioning system is delta t, the distance interval between the two positioning systems is L, and the target is far away from the two positioning systemsIf the vertical distance difference of the connecting line is R, the equivalent position error of the single time difference positioning system can be calculated to be approximate to
Wherein C is 3 × 10 8 m/s, according to the geometric configurations of two groups of positioning systems and targets, the positioning error delta X of the double stars can be approximately obtained
ΔX＝2R 2 CΔt/L 2 (2)
Also, although approximated, the overall accuracy can be used substantially as a reference for the overall design of the system. For example, three radio detection satellites in the earth synchronous belt form two time difference positioning systems, the time difference measurement precision is 600 nanoseconds, the phase difference between the two systems is 15 degrees, the equivalent distance interval is 11039 kilometers, the time difference cross positioning is carried out on the low-orbit solar synchronous satellite, the vertical distance is about 42165 kilometers, and the positioning error can be quickly obtained by about 5 kilometers according to the formula (2). According to the quantized positioning accuracy evaluation value, the approximate efficiency of the three-star positioning system can be rapidly determined to be 5 kilometers magnitude, and the overall design and requirement demonstration is supported.
(II) space-based short arc orbit determination precision rapid analysis
Since spatial object surveillance focuses on the long-term motion laws of objects, it is difficult to meet task requirements by positioning alone. Therefore, on the basis of the positioning error, the short arc orbit determination precision is further quickly evaluated according to the orbit error propagation theory.
On the basis of double-star sight line cross positioning and three-star radio time difference positioning, short arc data with the observation time length delta T are obtained for a certain space target, and short arc orbit determination is carried out. In short arc orbit determination, a semi-major axis of an orbit is particularly important, orbit determination accuracy and prediction errors are directly determined, short arc orbit determination results can be obtained by adopting a simple Gaussian method, a Laplace method and the like for short arcs which are subjected to cross positioning to obtain target position vectors, but orbit determination accuracy evaluation is very difficult, and a large amount of simulation analysis is needed.
Mainly determining the track tracing error of the track according to the semimajor axis, and deducing the relation of the track tracing position error delta R brought by the observation time length delta T of the semimajor axis error delta a by using a two-body track error propagation equation as follows:
where μ is the earth's gravitational constant and a is the approximate target orbit semi-major axis. In general, it can be assumed that the position error Δ X of the cross-positioning is mainly concentrated in the along-track direction, and the along-track error Δ R ≈ Δ X is set, then the semi-major axis error of the short arc tracking can be described as:
taking the two-satellite positioning as an example, the observation time is 15 minutes, the semi-major axis of the synchronous orbit target is about 42165 kilometers, and when the two-satellite positioning error is 6 kilometers, the short arc orbit determination semi-major axis error can be rapidly obtained by using the formula (4) and is about 60 kilometers. Taking the three-star time difference positioning as an example, the observation time length is 5 minutes, the semimajor axis of the sun synchronization orbit target is about 7178 kilometers, and when the three-star positioning error is 5 kilometers, the error of the semimajor axis of the short arc orbit determination can be quickly obtained by using the formula (4) and is about 10 kilometers magnitude. The quantitative analysis and the numerical simulation analysis are basically consistent in magnitude order, can be used for quick efficiency evaluation of a multi-satellite positioning and orbit determination system, has higher actual value for supporting overall design, and has great significance for the cost-efficiency ratio and the system contribution rate of an overall designer of a space-based monitoring satellite system for quickly analyzing the system.
According to the above analysis, a specific technical solution of the multi-satellite positioning and orbit determination precision rapid analysis method for space-based space target monitoring in the embodiment of the present invention is shown in fig. 1, and includes the following steps:
step 1, according to the geometric configuration and the measurement error of the satellite, the formula (1) or the formula (2) is selected respectively by combining the sight line cross positioning and the time difference positioning types of the satellite, and the multi-satellite positioning error delta X is obtained through rapid analysis.
And 2, rapidly calculating the semi-major axis error of the short arc orbit determination by using the observation arc section time length, the target orbit and the multi-satellite positioning error delta X and using the formula (4), and effectively evaluating the multi-satellite positioning orbit determination efficiency.
The design implementation method for the multi-satellite positioning orbit determination precision rapid analysis of space-based space target monitoring provided by the invention is finished.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present 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 (3)
1. A multi-satellite positioning and orbit determination precision rapid analysis method for space-based space target monitoring is characterized by comprising the following steps:
according to the geometric configuration and the measurement error of the satellite, the multi-satellite positioning error delta X is obtained by analysis in combination with the type of the satellite sight line cross positioning and the time difference positioning, and the method specifically comprises the following steps:
if the satellite sight line cross positioning is double-star sight line cross positioning, the angle measurement error of the pitch angle and the azimuth angle of a single star is delta alpha, the distance interval of double stars is L, and the vertical distance difference between a target and a double-star connecting line is R, the positioning error delta X of the double stars is as follows: Δ X ═ 2R 2 Δα/L；
If the time difference positioning is the three-star radio time difference positioning, two time difference positioning systems are formed by the three-star middle edge satellite and the middle satellite, the time difference measurement error of the single time difference positioning system is delta t, the distance interval between the two positioning systems is L, the vertical distance difference of the target from the connecting line of the two positioning systems is R, and the obtained positioning error delta X of the three-star is delta X-2R 2 CΔt/L 2 Wherein the speed of light C is 3 × 10 8 m/s；
Using the observation arc duration, the target orbit and the multi-satellite positioning error DeltaX, using the formula
Calculating semi-major axis error delta a of short arc orbit determination, and effectively evaluating multi-star positioning orbit determination efficiency, wherein mu is an earth gravity constant, a is an approximate target orbit semi-major axis, and delta T isAnd (5) observing the time length.
2. The method as claimed in claim 1, wherein the two-star line-of-sight cross-location is adopted, and two 800 km sun-synchronous orbit monitoring satellites are adopted to observe the geosynchronous orbit at 42165 km with a smooth observation precision of 5 angular seconds.
3. The method as claimed in claim 2, wherein the three-star radio time difference positioning uses three radio detection satellites in the earth synchronous belt to form two sets of time difference positioning systems, the time difference measurement accuracy Δ t is 600 nanoseconds, the phase difference between the two sets of systems is 15 degrees, the equivalent distance interval is 11039 km, and the time difference cross positioning is performed on the low-orbit solar synchronous satellite, and the vertical distance is about 42165 km.
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