High-orbit satellite-based GNSS missing navigation signal geometry observation error correction method and system

Abstract

The application belongs to the technical field of satellite navigation and positioning, and specifically discloses a high-orbit satellite-borne GNSS missing navigation signal geometric observation error correction method and system. The method comprises the following steps: obtaining the original observation data of the high-orbit satellite-borne single-frequency GNSS missing navigation signal, and constructing a non-difference non-combined geometric observation model; calculating the total electron content of the GNSS missing navigation signal on the ionosphere and the ionosphere propagation path, and then obtaining the signal delay error correction quantity; establishing a random model considering the signal tangent point height, and reducing the weight of the observation values seriously affected by the ionosphere / plasmosphere delay; and using the corrected observation values to perform high-orbit satellite precise orbit determination. The application is aimed at the plasmosphere delay effect specific to high-orbit satellites, and significantly weakens the systematic measurement bias by combining model correction with random model refinement, so that the orbit determination accuracy of high-orbit IGSO / GEO satellites can be improved from the meter level to the sub-meter level, thereby providing technical support for high-precision earth observation tasks of high-orbit satellites.

Description

Technical Field

[0001] This invention relates to the field of satellite navigation and positioning technology, and in particular to a method and system for correcting geometric observation errors based on missing navigation signals from high-orbit GNSS satellites. Background Technology

[0002] With the continuous expansion of human space activities, high-orbit satellites (such as GEO and IGSO satellites) are playing an increasingly important role in fields such as communication, navigation, and remote sensing. Their precise orbit determination accuracy directly determines mission effectiveness. Traditional ground-based measurement methods have limitations such as short observation arcs and reliance on the distribution of global stations, while spaceborne GNSS technology, with its advantages of all-weather operation, high precision, and low cost, has become the mainstream method for precise orbit determination of high-orbit satellites.

[0003] However, high-orbit satellites typically operate within GNSS constellations, and their receivers primarily capture and track "missing navigation signals" (also known as sidelobe signals) transmitted by navigation satellites. Unlike ground-based or low-orbit users, these signals have longer propagation paths, traversing the Earth's ionosphere (approximately 50-1000 km) and the outer plasmasphere (approximately 1000-36000 km). Existing research indicates that even for single-frequency receivers, free electrons in the plasmasphere can cause signal delay errors on the order of meters or even tens of meters, leading to significant systematic biases in orbit determination results. Currently, high-orbit satellites commonly employ single-frequency receivers to reduce costs, while conventional error processing methods, such as simply removing low elevation angle data or using semi-summary combined models, either weaken the already scarce geometric constraints or amplify observational noise, making it difficult to meet the decimeter-level orbit determination requirements.

[0004] Therefore, there is an urgent need for a method that can accurately model and correct the ionospheric and plasmaspheric delay errors in the leaked navigation signals of high-orbit satellites, so as to improve the precision orbit determination accuracy of high-orbit satellites. Summary of the Invention

[0005] The purpose of this invention is to provide a method and system for correcting geometric observation errors of high-orbit spaceborne GNSS missing navigation signals. The method organically combines physical model correction with a precise stochastic model, aiming to systematically solve the adverse effects of plasma layer delay on the observation accuracy of missing navigation signals in high-orbit environments.

[0006] To achieve the above objectives, this invention provides a method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS, comprising the following steps: S1. Obtain the raw observation data of the GNSS missing navigation signal tracked by the onboard single-frequency receiver of the high-orbit satellite, and construct a single-frequency non-differential non-combined geometric observation model after preprocessing; S2. Calculate the total electron content along the propagation path of the GNSS leaky navigation signal, and calculate the plasma layer delay error correction amount based on the total electron content; S3. Establish a stochastic model of observations that takes into account the height of the signal tangent point, and determine the weight of each observation based on the height of the tangent point; S4. Use the plasma layer delay error correction amount to correct the systematic error of the observations in the non-differential non-combined geometric observation model, and combine it with the observation stochastic model to perform precise orbit determination of high-orbit satellites.

[0007] Preferably, in S1, the high-orbit satellite is a geostationary orbit GEO satellite or an inclined geosynchronous orbit IGSO satellite, and the GNSS navigation signal includes the GPS L1 frequency signal and / or the BDS B1I frequency signal; The acquired raw observation data includes single-frequency pseudorange and carrier phase observations, and the observation noise is extracted using the triple difference method; For four adjacent epochs pseudo-distance and carrier phase The formula for calculating the higher order difference is: ; In the formula, and These represent the satellite end and the receiver end, respectively. For the receiver end to satellite end pseudorange, For receiver End to satellite carrier phase, , , and The first , , and Receiver end at epoch to satellite end pseudorange, , , and The first , , and Receiver at an epoch End to satellite carrier phase, and These represent the observation noise of single-frequency pseudorange and carrier phase, respectively; According to the law of error propagation: ; In the formula, and These represent the measurement noise after three differences and the measurement noise without differences, respectively.

[0008] Preferably, in S1, the constructed single-frequency non-differential non-combined geometric observation model uses the ionospheric and plasmaspheric delays as parameters to be determined for a given navigation satellite. At frequency pseudodistance on and carrier phase Its observation equation is: ; In the formula, This is the geometric distance from the phase center of the navigation satellite's transmitting antenna to the phase center of the receiver antenna. The speed of light; and These are receiver clock bias and navigation satellite clock bias, respectively. This is the first-order term of ionospheric delay; and These are the receiver-side pseudorange and phase hardware delay, respectively. and These are pseudorange and phase hardware delay at the navigation satellite end, respectively. The carrier wavelength; For carrier phase integer ambiguity; and These are pseudorange and phase observation noise, respectively.

[0009] Preferably, when a high-orbit satellite simultaneously receives signals from multiple systems, the multi-system observation equation is expressed as: ; In the formula, superscript This indicates different GNSS satellite navigation systems.

[0010] Preferably, in S2, an empirical model of the ionosphere and plasmasphere is introduced, and a multi-layer assumption integration method is used to calculate the total electron content along the propagation path of the GNSS leaky navigation signal. Based on the total electron content, the plasmasphere delay error correction is calculated. Specifically: First, a non-differential, non-combined model of GNSS missing navigation signals is established, and its expression is: ; In the formula, This refers to the delay caused by the ionosphere and plasma layer; The formula for calculating the delay along the signal propagation path is: ; In the formula, The total electron content along the signal propagation path. For frequency; Then, the ionosphere and plasma layer are divided into multiple thin layers in the vertical direction. The product of the electron density in each thin layer and the signal propagation path length is integrated, and the total electron content along the signal propagation path is obtained by summing them up. Based on total electron content The delay error correction amounts for the ionosphere and plasma layer were calculated.

[0011] Preferably, in S3, the expression for the observed stochastic model that takes into account the signal tangent height is: ; In the formula, For the weight of the observations, As the initial weights for the observations, The height of the tangent point above the ground along the observation transmission path. This is the threshold height for the tangent point.

[0012] Preferably, in S3, for tangent heights lower than a preset threshold... The GNSS observations are downweighted, and the tangent point height is higher than a preset threshold. GNSS observations are given high weight.

[0013] Preferably, in S4, the plasma layer delay calculated in S2 is used to correct the systematic error of the original observation value, and the least squares batch processing solution is performed according to the weight matrix determined in S3. The parameters to be estimated include the initial state parameters of the high-orbit satellite, the receiver clock error parameters, the carrier phase integer ambiguity, and the solar radiation pressure perturbation parameters.

[0014] This invention also provides a geometric observation error correction system based on missing navigation signals from high-orbit spaceborne GNSS, used to implement the above method, including: The data acquisition module is used to acquire raw observation data of the onboard GNSS navigation signals of high-orbit satellites. The error correction module is used to calculate the plasma layer delay error correction based on the IRI-Plas or GCPM model and the multilayer hypothesis integration method, and to establish a stochastic model that takes into account the tangent height. The orbit determination module is used to estimate precise orbit determination parameters using corrected observation data.

[0015] Therefore, the present invention employs the above-mentioned method and system for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS, and the beneficial technical effects are as follows: (1) This invention significantly improves the measurement accuracy and availability of high-orbit satellite-borne GNSS missing navigation signals by combining "hard correction" based on physical models with "soft weighting" based on data quality.

[0016] (2) This invention can improve the three-dimensional orbit determination accuracy of IGSO satellites from 4.47 meters to below 2.34 meters, an improvement of more than 47%, providing strong support for applications that require high-precision orbits, such as high-orbit SAR imaging.

[0017] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0018] Figure 1 This is an overall flowchart of an embodiment of the present invention based on the geometric observation error correction method for missing navigation signals of high-orbit spaceborne GNSS; Figure 2 This is a schematic diagram of plasma layer partitioning based on an embodiment of the geometric observation error correction method for missing navigation signals of high-orbit spaceborne GNSS according to the present invention. Detailed Implementation

[0019] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0020] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning as understood by one of ordinary skill in the art to which this invention pertains.

[0021] This invention primarily addresses the ionospheric and plasmaspheric delay errors present in GNSS missed navigation signals on high-orbit satellites, proposing a high-precision method for correcting geometric observation errors in these signals. This method innovatively configures parameters such as the propagation path, signal frequency, and observation time of the GNSS missed navigation signal observations. It utilizes a plasmaspheric delay error modeling module to generate electron density profile information, considering factors such as electron density variations at different altitudes, signal tangent height, and solar and geomagnetic activity indices. Different systematic error correction values ​​are assigned to the plasmaspheric delay amounts under different propagation paths, thus completing the correction of GNSS missed navigation signal delay errors under different space environments. A precise orbit determination module is used to estimate the parameters and verify the accuracy of the corrected observations, helping high-orbit satellites eliminate systematic measurement biases and achieve meter-level or even sub-meter-level precise orbit determination.

[0022] like Figure 1 As shown, the method for correcting geometric observation errors of missing navigation signals from high-orbit spaceborne GNSS includes the following steps: S1. Obtain the raw observation data of the GNSS leaked navigation signal tracked by the onboard single-frequency receiver of the high-orbit satellite, and construct a single-frequency non-differential non-combined geometric observation model after preprocessing.

[0023] The high-orbit satellite of this invention is a geostationary orbit (GEO) satellite or an inclined geosynchronous orbit (IGSO) satellite, and the GNSS navigation signal includes GPS L1 frequency signal and / or BDS B1I frequency signal.

[0024] In this implementation, the receiver simultaneously tracks the missing navigation signals at both the GPS L1 frequency (1575.42 MHz) and the BDS B1I frequency (1561.098 MHz). The raw observation data acquired includes single-frequency pseudorange and carrier phase observations, with a data sampling interval of 30 seconds.

[0025] During preprocessing, data quality can be assessed by calculating the geometric observation noise of the missing navigation signal. For high-orbit satellites, the triple-difference method is generally considered to be effective in extracting observation noise.

[0026] For four adjacent epochs pseudo-distance and carrier phase The formula for calculating the higher order difference is: ; In the formula, and These represent the satellite end and the receiver end, respectively. For the receiver end to satellite end pseudorange, For receiver End to satellite carrier phase, , , and The first , , and Receiver end at epoch to satellite end pseudorange, , , and The first , , and Receiver at an epoch End to satellite carrier phase, and These represent the observation noise of single-frequency pseudorange and carrier phase, respectively.

[0027] According to the law of error propagation, we can obtain: ; In the formula, and These represent the measurement noise after three differences and the measurement noise without differences, respectively.

[0028] The single-frequency non-difference non-combined geometric observation model constructed in this embodiment takes the delay of the ionosphere and plasma layer as parameters to be determined, rather than simply ignoring them or eliminating them by combining observation values.

[0029] For a certain navigation satellite At frequency pseudodistance on and carrier phase Its observation equation is: ; In the formula, This is the geometric distance from the phase center of the navigation satellite's transmitting antenna to the phase center of the receiver antenna. The speed of light; and These are receiver clock bias and navigation satellite clock bias, respectively. This is the first-order term of ionospheric delay; and These are the receiver-side pseudorange and phase hardware delay, respectively. and These are pseudorange and phase hardware delay at the navigation satellite end, respectively. The carrier wavelength; For carrier phase integer ambiguity; and These are pseudorange and phase observation noise (and other unmodeled errors), respectively. In the above equations, correction terms for antenna phase center offset and variation, phase entanglement, and relativistic effects are not explicitly listed; they need to be corrected using a priori models in actual processing.

[0030] With the development of GNSS multi-systems, high-orbit satellites can simultaneously receive signals from multiple systems such as GPS, BDS, and Galileo. The multi-system observation equation can be expressed as: ; In the formula, superscript This indicates different GNSS satellite navigation systems.

[0031] For GNSS systems using Code Division Multiple Access (CDMA), the receiver hardware delay at the same frequency point within the same system is the same for all satellites. During joint orbit determination, an inter-system bias (ISB) parameter needs to be introduced between different systems to reduce the receiver clock bias parameters of multiple systems to the reference system. For receivers that support multiple frequencies, the optimal linear combination needs to be selected based on wavelength, ionosphere, and noise amplification factor to further improve orbit determination accuracy.

[0032] S2. Introduce internationally mainstream empirical models for the ionosphere and plasmasphere, extending them to the international reference ionospheric model IRI-Plas or the global core plasmasphere model GCPM. Employ a multi-level assumption integration method to calculate the total electron content along the propagation path of the GNSS leaky navigation signal, and calculate the plasmasphere delay error correction based on the total electron content. Specifically: Based on a single-frequency non-differential non-combined geometric observation model, this invention proposes a plasma layer delay error correction model based on multi-layer assumptions. First, a non-differential non-combined model of GNSS leaky navigation signals is established, the expression of which is: ; In the formula, This represents the delay caused by the ionosphere and plasma layer.

[0033] The formula for calculating the delay along the signal propagation path is: ; In the formula, The total electron content along the signal propagation path. The frequency can be calculated using empirical models such as GCPM or IRI-Plas. Since the transmission path of high-orbit navigation signals differs from that of ground users, this invention employs the plasma layer multilayer assumption method. This assumption assumes that it is impossible to accurately obtain the changing structure of free electrons in the plasma layer along the propagation path, and that it is difficult to achieve a detailed model of the three-dimensional spatial distribution of plasma layer electron density. Simultaneously, it ignores the anisotropy of plasma layer electron density in the horizontal direction.

[0034] Therefore, the ionosphere and plasma layer can be vertically divided into multiple thin layers, each 500 kilometers thick. By integrating the product of the electron density and the signal propagation path length in each thin layer, the total electron content along the signal propagation path can be obtained. Based on total electron content The delay error correction amounts for the ionosphere and plasma layer were calculated.

[0035] like Figure 2 As shown, under the assumption of a multilayer plasma layer, the plasma layer is divided into layers from top to bottom. The distribution of electron density in each layer of the plasma layer can be obtained by integration: ; In the formula, and These represent the positions of the GNSS satellite transmitter and the high-orbit satellite receiver in the Earth-fixed system, respectively. The electron density at the location between the satellite and the receiver. The electron density is calculated using the GCPM and IRI-Plas empirical models. For the signal transmission path in the th The length of the propagation path within the plasma layer represented by the thin layer, and The represented electron density regions are corresponding. The number of layers in the hypothetical plasma layer.

[0036] S3. Establish a stochastic model of observations that takes into account the height of the signal tangent point, and determine the weight of each observation based on the height of the tangent point.

[0037] Although the IRI-Plas empirical model has high accuracy above 1000 km, it still has some residual error in the ionospheric region below 1000 km. Furthermore, low-altitude signals are severely affected by the ionosphere. To reduce the adverse effects of unmodeled delays in low-altitude observations on orbit determination, while preserving as much of the contribution of high-altitude, high-quality observation data to the geometric configuration as possible, this invention constructs a method based on the signal tangent height. The specific expression for the exponential stochastic model with variable tangent height weighting is: ; In the formula, For the weight of the observations, As the initial weights for the observations, The height of the tangent point above the ground along the observation transmission path. This is the threshold height for the tangent point.

[0038] In this embodiment, for the tangent height being lower than a preset threshold GNSS observations are severely affected by ionospheric / plasmosphere delay, therefore they are downweighted, especially for tangent point heights higher than a preset threshold. The GNSS observations are given high weight, which effectively suppresses the influence of unmodeled residual errors while ensuring the geometric configuration.

[0039] In this embodiment, when the tangent height threshold is reached... Setting the threshold to 2000 km is generally considered to reduce the impact of ionospheric delay on the accuracy of GNSS signal measurements; when the threshold is set to 6000 km, it is considered to reduce the impact of ionospheric delay and plasmaspheric delay in the outer space environment while ensuring the highest availability of geometric observation data.

[0040] S4. The plasma layer delay error correction is used to correct the systematic error of the observations in the non-differential non-combined geometric observation model, and the observations are combined with the observation stochastic model to perform precise orbit determination of high-orbit satellites, and output high-precision orbit products.

[0041] Specifically: The plasma layer delay calculated in S2 is used to correct systematic errors in the original observations, and least-squares batch processing is performed based on the weight matrix determined in S3. The parameters to be estimated include: The high-orbit satellite has a total of 6 initial state parameters at the reference epoch: position (3) and velocity (3).

[0042] The receiver clock bias parameter is estimated for each epoch and treated as white noise.

[0043] Carrier phase integer ambiguity, one floating-point solution is estimated for each consecutive tracking arc segment.

[0044] The solar radiation pressure perturbation parameters were estimated using the ECOM 9-parameter model.

[0045] In addition, the present invention also includes using observation data from dual receivers carried by high-orbit satellites to construct inter-station double-difference observation equations for joint precise orbit determination.

[0046] This invention also provides a geometric observation error correction system based on missing navigation signals from high-orbit spaceborne GNSS, used to implement the above method, including: The data acquisition module is used to acquire raw observation data of the onboard GNSS navigation signals of high-orbit satellites.

[0047] The error correction module is used to calculate the plasma layer delay error correction based on the IRI-Plas or GCPM model and the multilayer hypothesis integration method, and to establish a stochastic model that takes into account the tangent height.

[0048] The orbit determination module is used to estimate precise orbit determination parameters using corrected observation data.

[0049] After the calculation is completed, the precise orbit product of the high-orbit satellite is output. The orbit accuracy is evaluated by comparing overlapping arc segments (adjacent 72-hour orbit determination arc segments overlap by 24 hours) and statistically analyzing the carrier phase verification residual. Using the method of this embodiment, taking a certain high-orbit IGSO satellite as an example, the carrier phase verification residual RMS value decreased from 112.89 mm before correction to 69.83 mm, and the three-dimensional overlapping arc segment orbit error RMS value decreased from 4.47 m to 2.34 m, with an accuracy improvement of approximately 48%. The results are shown in Table 1.

[0050] Table 1. Statistics on Residual and Overlapping Arc Accuracy Based on Different Error Correction Strategies

[0051] Therefore, this invention adopts the above-mentioned geometric observation error correction method based on the high-orbit spaceborne GNSS missing navigation signal, uses the multi-layer hypothesis integration method to calculate the total electron content of the ionosphere and plasmasphere, and realizes adaptive weighting of the observation value based on the stochastic model of the tangent point height to carry out comprehensive error correction on the high-orbit spaceborne GNSS missing navigation signal, which significantly weakens the systematic deviation caused by the plasmasphere delay and effectively improves the precision orbit determination effect of high-orbit satellites.

[0052] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A method for correcting geometric observation errors of missing navigation signals from high-orbit spaceborne GNSS, characterized in that, Includes the following steps: S1. Obtain the raw observation data of the GNSS missing navigation signal tracked by the onboard single-frequency receiver of the high-orbit satellite, and construct a single-frequency non-differential non-combined geometric observation model after preprocessing; S2. Calculate the total electron content along the propagation path of the GNSS leaky navigation signal, and calculate the plasma layer delay error correction amount based on the total electron content; S3. Establish a stochastic model of observations that takes into account the height of the signal tangent point, and determine the weight of each observation based on the height of the tangent point; S4. Use the plasma layer delay error correction amount to correct the systematic error of the observations in the non-differential non-combined geometric observation model, and combine it with the observation stochastic model to perform precise orbit determination of high-orbit satellites.

2. The method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS according to claim 1, characterized in that, In S1, the high-orbit satellites are geostationary GEO satellites or inclined geosynchronous orbit IGSO satellites, and the GNSS missing navigation signals include GPS L1 frequency signals and / or BDS B1I frequency signals. The acquired raw observation data includes single-frequency pseudorange and carrier phase observations, and the observation noise is extracted using the triple difference method; For four adjacent epochs pseudo-distance and carrier phase The formula for calculating the higher order difference is: ； In the formula, and These represent the satellite end and the receiver end, respectively. For the receiver end to satellite end pseudorange, For receiver End to satellite carrier phase, , , and The first , , and Receiver end at epoch to satellite end pseudorange, , , and The first , , and Receiver at an epoch End to satellite carrier phase, and These represent the observation noise of single-frequency pseudorange and carrier phase, respectively; According to the law of error propagation: ； In the formula, and These represent the measurement noise after three differences and the measurement noise without differences, respectively.

3. The method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS according to claim 2, characterized in that, In S1, the constructed single-frequency non-difference non-combined geometric observation model uses the ionospheric and plasmaspheric delays as parameters to be determined for a given navigation satellite. At frequency pseudodistance on and carrier phase Its observation equation is: ； In the formula, This is the geometric distance from the phase center of the navigation satellite's transmitting antenna to the phase center of the receiver antenna. The speed of light; and These are receiver clock bias and navigation satellite clock bias, respectively. This is the first-order term of ionospheric delay; and These are the receiver-side pseudorange and phase hardware delay, respectively. and These are pseudorange and phase hardware delay at the navigation satellite end, respectively. The carrier wavelength; For carrier phase integer ambiguity; and These are pseudorange and phase observation noise, respectively.

4. The method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS according to claim 2, characterized in that, When a high-orbit satellite simultaneously receives signals from multiple systems, the multi-system observation equation is expressed as: ； In the formula, superscript This indicates different GNSS satellite navigation systems.

5. The method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS according to claim 3, characterized in that, In S2, empirical models of the ionosphere and plasmasphere are introduced. A multi-level assumption integration method is used to calculate the total electron content along the propagation path of the GNSS leaky navigation signal. Based on the total electron content, the plasmasphere delay error correction is calculated. Specifically: First, a non-differential, non-combined model of GNSS missing navigation signals is established, and its expression is: ； In the formula, This refers to the delay caused by the ionosphere and plasma layer; The formula for calculating the delay along the signal propagation path is: ； In the formula, The total electron content along the signal propagation path. For frequency; Then, the ionosphere and plasma layer are divided into multiple thin layers in the vertical direction. The product of the electron density in each thin layer and the signal propagation path length is integrated, and the total electron content along the signal propagation path is obtained by summing them up. Based on total electron content The delay error correction amounts for the ionosphere and plasma layer were calculated.

6. The method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS according to claim 5, characterized in that, In S3, the expression for the observed stochastic model that takes into account the signal tangent height is: ； In the formula, For the weight of the observations, As the initial weights for the observations, The height of the tangent point above the ground along the observation transmission path. This is the threshold height for the tangent point.

7. The method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS according to claim 6, characterized in that, In S3, for tangent heights below a preset threshold The GNSS observations are downweighted, and the tangent point height is higher than a preset threshold. GNSS observations are given high weight.

8. The method for correcting geometric observation errors based on missing navigation signals from high-orbit spaceborne GNSS according to claim 1, characterized in that, In S4, the plasma layer delay calculated in S2 is used to correct the systematic error of the original observations, and the least squares batch processing is performed based on the weight matrix determined in S3. The parameters to be estimated include the initial state parameters of the high-orbit satellite, the receiver clock error parameters, the carrier phase integer ambiguity, and the solar radiation pressure perturbation parameters.

9. A geometric observation error correction system based on missing navigation signals from high-orbit spaceborne GNSS, used to implement the method described in any one of claims 1-8, characterized in that, include: The data acquisition module is used to acquire raw observation data of the onboard GNSS navigation signals of high-orbit satellites. The error correction module is used to calculate the plasma layer delay error correction based on the IRI-Plas or GCPM model and the multilayer hypothesis integration method, and to establish a stochastic model that takes into account the tangent height. The orbit determination module is used to estimate precise orbit determination parameters using corrected observation data.

Images