Space environment incentive graph evaluation method and system for spacecraft orbit-related affairs

Abstract

The present invention belongs to the field of aerospace data processing technology, and specifically relates to a space environment incentive map evaluation method for spacecraft orbit-related matters, comprising: step 1) obtaining orbit and space environment data sets in a space debris early warning mission; step 2) screening out multiple close-range rendezvous targets based on a pre-set rendezvous distance threshold criterion to form a dangerous target list; step 3) for each rendezvous target, drawing a space environment incentive map of space debris collision risk with a main spacecraft aerodynamic adjustment coefficient as the horizontal coordinate and aerodynamic adjustment coefficient of the rendezvous target as the vertical coordinate, with a color bar representing a collision probability value, and drawing a reachable domain on the space environment incentive map; step 4) repeating the above step 3) to obtain a space environment incentive map for each rendezvous target, obtain a space environment incentive map set, classify the maps, obtain classification results, and then organize the results for user terminal evaluation and decision-making.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace data processing technology, and in particular relates to a method and system for evaluating a space environment incentive graph for spacecraft orbit-related matters. Background Art

[0002] Spacecraft orbit-related issues refer to those related to orbit prediction and design during space missions. These include, for example, spacecraft collision risk assessment, fallout and re-entry time and location prediction, and orbit design. With the advancement of orbital theory, thermospheric atmospheric density prediction has become the largest source of error in the prediction and determination of low-orbit spacecraft orbits. However, the assessment results of these orbit-related issues generate uncertainty, making them difficult to quantify and describe, and thus unable to guide effective engineering responses.

[0003] Existing space environment incentive graph evaluation methods mainly rely on the box method based on the three-dimensional intersection distance and the probabilistic method based on the collision probability. However, the existing methods have the problem of inaccurate description of collision risk and are unable to judge the impact of factors such as space environment disturbance and ballistic coefficient error on the intersection risk. Summary of the Invention

[0004] In order to solve the problems existing in the prior art, the present invention proposes a space environment incentive diagram evaluation method for spacecraft orbit-related matters. The method is suitable for spacecraft orbit-related matters such as space debris collision risk assessment, fall and re-entry time and location prediction, and orbit design.

[0005] The present invention provides a space environment incentive graph evaluation method for spacecraft orbit-related matters, the method comprising:

[0006] Step 1) In the space debris early warning mission, obtain orbital and space environment datasets;

[0007] Step 2) Extract the orbital positions and velocities of the primary spacecraft and the rendezvous target from the acquired orbital and space environment datasets, perform conventional space debris early warning calculations, and use pre-set criteria to screen out multiple close rendezvous targets to form a list of dangerous targets.

[0008] Step 3) For each rendezvous target in the list of dangerous targets, plot a space environment excitation diagram of the space debris collision risk, with the primary spacecraft aerodynamic adjustment coefficient as the horizontal axis and the rendezvous target aerodynamic adjustment coefficient as the vertical axis. The color bar represents the collision probability value, and the reachable domain is plotted on the space environment excitation diagram.

[0009] Step 4) Repeat step 3) above to obtain a space environment excitation map for each intersection target, obtain a space environment excitation map set, classify it, obtain the classification results, and then organize them for user terminal evaluation and decision-making.

[0010] As one of the improvements to the above technical solution, the orbital and space environment data set includes but is not limited to: the orbital position, velocity and space environment Kp, F10.7 index of the main spacecraft and the rendezvous target; wherein the rendezvous target is background space debris.

[0011] As one of the improvements to the above technical solution, step 2) specifically includes:

[0012] From the acquired orbital and space environment data sets, the orbital positions and velocities of the main spacecraft and the rendezvous target are extracted to perform conventional space debris early warning calculations:

[0013] During the warning time ΔT set by the user, a rough screening is performed using the orbital altitudes of the main spacecraft and background space debris;

[0014] The orbital altitude of the main spacecraft is within the range of ±Δh. It is determined whether the orbit of the main spacecraft intersects with the orbit of the background debris.

[0015] If there is an intersection between the main spacecraft and the rendezvous target, the background space debris is retained and used as a rough rendezvous target and stored in the coarse screening target list;

[0016] If there is no intersection between the main spacecraft and the rendezvous target, the background space debris is eliminated;

[0017] Within ΔT, the orbital position of the main spacecraft and each coarse-screened target in the coarse-screened target list is determined with a step size of s. According to the orbital position and speed of the two, the intersection distance between the main spacecraft and each coarse-screened target is determined, and the closest intersection distance set between the main spacecraft and each coarse-screened target is formed. Where i = 1, 2…n;

[0018] The intersection distance threshold r is set in advance thresh As the criterion, it is determined whether each value in the nearest intersection distance set is less than the preset intersection distance threshold r thresh ;

[0019] If the i-th intersection distance Less than r thresh , it will be regarded as a space target and stored in the dangerous target list;

[0020] If the i-th intersection distance Greater than or equal to r thresh , delete it.

[0021] As one of the improvements to the above technical solution, step 3) specifically includes:

[0022] According to the orbital atmospheric density of the main spacecraft and the ballistic coefficient of the main spacecraft, they are multiplied and coupled in the drag equation;

[0023]

[0024] Among them, F d1 The aerodynamic force of the main spacecraft; ρ1 is the orbital atmospheric density of the main spacecraft; BC1 is the ballistic coefficient of the main spacecraft; v r is the relative atmospheric speed of the rendezvous target;

[0025] According to the main spacecraft aerodynamic adjustment coefficient α1, the collision probability Pc1 of the main spacecraft is calculated;

[0026] Pc1=f(α1×F d1 )

[0027] By adjusting the main spacecraft aerodynamic adjustment coefficient α1, the main spacecraft aerodynamic force F is adjusted bidirectionally. d1 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas;

[0028] According to the orbital atmospheric density of the rendezvous target and the ballistic coefficient of the rendezvous target, they are multiplied and coupled in the drag equation;

[0029]

[0030] Among them, F d2 is the aerodynamic force of the rendezvous target; ρ2 is the orbital atmospheric density of the rendezvous target; BC2 is the ballistic coefficient of the rendezvous target; v r is the relative atmospheric speed of the rendezvous target;

[0031] According to the aerodynamic adjustment coefficient α2 of the rendezvous target, the collision probability Pc2 of the rendezvous target is calculated;

[0032] Pc2=f(α2×F d2 )

[0033] By adjusting the aerodynamic adjustment coefficient α2 of the rendezvous target, the aerodynamic force F of the rendezvous target is adjusted in both directions. d2 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas;

[0034] Therefore, a space environment excitation map of the space debris collision risk is drawn for each rendezvous target, with the main spacecraft aerodynamic adjustment coefficient as the horizontal coordinate and the rendezvous target aerodynamic adjustment coefficient and collision probability as the vertical coordinate. In the drawn space environment excitation map, an interval range is formed from the minimum collision probability area to the maximum collision probability area; and according to the upper and lower limits of the space environment forecast, a reachable domain is drawn on the space environment excitation map.

[0035] As one of the improvements to the above technical solution, step 4) specifically includes:

[0036] For the space environment excitation diagram of the i-th rendezvous target, the Pc value calculated when α1 = 0 and α2 = 0 is used as the current collision probability value; where α1 is the aerodynamic adjustment coefficient of the main spacecraft and α2 is the aerodynamic adjustment coefficient of the rendezvous target;

[0037] If the current collision probability value is in the Pc maximum value area, the incentive graph is classified as a low-collision risk incentive graph;

[0038] If the current collision probability value is in the Pc minimum area, the incentive graph is classified as a low-collision risk incentive graph;

[0039] If both adjustment coefficients are between 10 -0.6 ~10 0.6 When the range changes, the collision probability is less than 1×10 -5 , is not sensitive to space weather changes, and the rendezvous risk is not affected by the development of solar storms;

[0040] Collision probability Pc>5×10 -5 , and the reachable domain exceeds the set collision avoidance threshold, the incentive graph is classified as a high-risk incentive graph for collision, and the emergency plan needs to be activated;

[0041] The above process is repeated for each intersection target, and the classification results are sorted out for evaluation and decision-making by the user terminal.

[0042] The present invention also provides a space environment incentive map evaluation system for spacecraft orbit-related matters, the system comprising: a data acquisition module, a target list acquisition module and an incentive map drawing module;

[0043] The data acquisition module is used to obtain orbit and space environment data sets in the space debris early warning mission;

[0044] The target list acquisition module is used to extract the orbital position and velocity of the main spacecraft and the rendezvous target from the acquired orbital and space environment data sets, perform conventional space debris early warning calculations, and use the pre-set collision distance as a criterion and the rendezvous distance as the rendezvous distance to screen out multiple close-range rendezvous targets to form a dangerous target list;

[0045] The excitation map drawing module is used to draw a space environment excitation map of space debris collision risk for each rendezvous target in the dangerous target list, using the main spacecraft aerodynamic adjustment coefficient as the horizontal coordinate and the aerodynamic adjustment coefficient of the rendezvous target as the vertical coordinate, with the color bar representing the collision probability value, and draw a reachable domain on the space environment excitation map;

[0046] Repeat the process of the excitation map drawing module to obtain the space environment excitation map for each intersection target, obtain the space environment excitation map set, classify it, obtain the classification results, and then organize them for user terminal evaluation and decision-making.

[0047] The beneficial effects of the present invention compared with the prior art are:

[0048] 1. The method of the present invention can effectively quantify and assess the uncertainty of spacecraft orbit-related assessment results caused by changes in the space environment; effectively reduce the false alarm rate and missed alarm rate in space debris collision warning; and is of great significance for efficiently identifying potential risks and guiding aerospace engineering practice and decision-making;

[0049] 2. For matters related to spacecraft orbits, by bidirectionally changing the primary and secondary rendezvous target adjustment coefficients, the possible impact of aerodynamic forces on collision probability is simulated. Based on the distribution of maximum and minimum values ​​of collision probability, a space environment incentive diagram evaluation method for matters related to spacecraft orbits is given. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 A space environment incentive map for space debris collision risk obtained by a space environment incentive map assessment method for spacecraft orbit-related matters according to the present invention;

[0051] Figure 2 The present invention is a method flow chart of a space environment incentive diagram evaluation method for spacecraft orbit-related matters. DETAILED DESCRIPTION

[0052] The present invention will now be further described with reference to the accompanying drawings.

[0053] The present invention provides a space environment incentive diagram evaluation method for spacecraft orbit-related matters. For spacecraft orbit-related matters, based on the maximum and minimum distribution of collision probability, a simplified model of the impact of atmospheric damping on prediction is used. This method can effectively quantify and evaluate the uncertainty of the evaluation results of spacecraft orbit-related matters caused by changes in the space environment, which is of great significance for efficiently identifying potential risks and guiding aerospace engineering practice and decision-making.

[0054] like Figure 2 As shown, the method includes:

[0055] Step 1) In the space debris early warning mission, obtain orbital and space environment datasets;

[0056] The orbital and space environment data sets include but are not limited to: the orbital position, velocity and space environment Kp and F10.7 index of the main spacecraft and the rendezvous target; wherein the rendezvous target is background space debris.

[0057] Step 2) Extract the orbital position and velocity of the host spacecraft and the rendezvous target from the acquired orbital and space environment datasets, perform conventional space debris early warning calculations, and use a pre-set collision distance as a criterion and as the rendezvous distance to screen out multiple close-range rendezvous targets and form a list of dangerous targets. In this embodiment, the pre-set collision distance is 10 km.

[0058] Specifically, the orbital position and velocity of the main spacecraft and the rendezvous target are extracted from the acquired orbital and space environment data sets, and conventional space debris early warning calculations are performed:

[0059] During the warning time ΔT set by the user, a rough screening is performed using the orbital altitudes of the main spacecraft and background space debris;

[0060] The orbital altitude of the main spacecraft is within the range of ±Δh. It is determined whether the orbit of the main spacecraft intersects with the orbit of the background debris.

[0061] If there is an intersection between the main spacecraft and the rendezvous target, the background space debris is retained and used as a rough rendezvous target and stored in the coarse screening target list;

[0062] If there is no intersection between the main spacecraft and the rendezvous target, the background space debris is eliminated;

[0063] Within ΔT, the orbital position of the main spacecraft and each coarse-screened target in the coarse-screened target list is determined with a step size of s. According to the orbital position and speed of the two, the intersection distance between the main spacecraft and each coarse-screened target is determined, and the closest intersection distance set between the main spacecraft and each coarse-screened target is formed. Wherein, i=1, 2…n;

[0064] The intersection distance threshold r is set in advance thresh As the criterion, it is determined whether each value in the nearest intersection distance set is less than the preset intersection distance threshold r thresh ;

[0065] If the i-th intersection distance Less than r thresh , it will be regarded as a space target and stored in the dangerous target list;

[0066] If the i-th intersection distance Greater than or equal to r htresh , delete it.

[0067] Step 3) For each rendezvous target in the list of dangerous targets, draw a space environment excitation diagram of the space debris collision risk, with the main spacecraft aerodynamic adjustment coefficient as the horizontal axis and the aerodynamic adjustment coefficient and collision probability of the rendezvous target as the vertical axis, and mark the reachable domain on the space environment excitation diagram.

[0068] Specifically, according to the orbital atmospheric density of the main spacecraft and the ballistic coefficient of the main spacecraft, they are multiplied and coupled in the drag equation;

[0069]

[0070] Among them, F d1 The aerodynamic force of the main spacecraft; ρ1 is the orbital atmospheric density of the main spacecraft; BC1 is the ballistic coefficient of the main spacecraft; v r is the relative atmospheric speed of the rendezvous target;

[0071] According to the main spacecraft aerodynamic adjustment coefficient α1, the collision probability Pc1 of the main spacecraft is calculated;

[0072] Pc1=α1×F d1

[0073] By adjusting the main spacecraft aerodynamic adjustment coefficient α1, the main spacecraft aerodynamic force F is adjusted bidirectionally. d1 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas;

[0074] According to the orbital atmospheric density of the rendezvous target and the ballistic coefficient of the rendezvous target, they are multiplied and coupled in the drag equation;

[0075]

[0076] Among them, F d2 is the aerodynamic force of the rendezvous target; ρ2 is the orbital atmospheric density of the rendezvous target; BC2 is the ballistic coefficient of the rendezvous target; v r is the relative atmospheric speed of the rendezvous target;

[0077] According to the aerodynamic adjustment coefficient α2 of the rendezvous target, the collision probability Pc2 of the rendezvous target is calculated;

[0078] Pc2=α2×F d2

[0079] By adjusting the aerodynamic adjustment coefficient α2 of the rendezvous target, the aerodynamic force F of the rendezvous target is adjusted in both directions. d2 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas;

[0080] Therefore, a space environment excitation map of the space debris collision risk is drawn for each rendezvous target, with the main spacecraft aerodynamic adjustment coefficient as the horizontal coordinate and the rendezvous target aerodynamic adjustment coefficient and collision probability as the vertical coordinate. In the drawn space environment excitation map, an interval range is formed from the minimum collision probability area to the maximum collision probability area; and according to the upper and lower limits of the space environment forecast, a reachable domain is drawn on the space environment excitation map.

[0081] Among them, in the drag equation, changing any parameter will affect the aerodynamic force F d There are only two possibilities for this change, namely, increasing or decreasing. Therefore, to evaluate the aerodynamic modeling error and how to change the collision probability of the rendezvous event, the aerodynamic forces of the primary and secondary rendezvous targets (primary spacecraft and rendezvous target) can be adjusted bidirectionally by adjusting the coefficient α. The corresponding collision probability is calculated in a grid-like manner, with the primary spacecraft aerodynamic adjustment coefficient as the horizontal axis and the rendezvous target aerodynamic adjustment coefficient and collision probability as the vertical axis. The color bar with the numerical value describes the collision probability Pc value at the grid point, and the space environment incentive diagram of the space debris collision risk is drawn and obtained, as shown in the figure. Figure 1 As shown. According to the excitation diagram, the collision probability value in the current space environment and the change trend in the disturbance environment are judged. The reachable domain drawn is as follows Figure 1 The area indicated by the dotted line.

[0082] Figure 1 The space environment excitation diagram in [1] encompasses all possible error sources in aerodynamic modeling. In practice, given knowledge of parameters such as the area-to-mass ratio and drag coefficient of space objects, the impact of changes in collision probability caused by the space environment forecast can be refined and framed based on the space environment forecast. This is known as defining the reachable domain. For example, using a space environment index forecast level of three standard deviations to maintain a 99.73% confidence level, we can explore the reachable domain of the assessment results.

[0083] Step 4) Repeat step 3) to obtain a space environment excitation map for each intersection target, obtain a space environment excitation map set, classify it, obtain the classification results, and then organize them for user terminal evaluation and decision-making.

[0084] Specifically, for the space environment excitation map of the i-th rendezvous target, the corresponding collision probability is obtained according to the aerodynamic adjustment coefficient of the main spacecraft and the aerodynamic adjustment coefficient of the rendezvous target obtained at the current moment;

[0085] If the current collision probability value (i.e., the Pc value calculated when α1 = 0, α2 = 0) is in the Pc maximum value area, the excitation graph is classified as a low-collision risk excitation graph; any atmospheric drag modeling error caused by any space environment disturbance will reduce the probability;

[0086] If the current collision probability value is in the Pc minimum area, that is, below the threshold where evasive measures need to be taken, the excitation graph is classified as a low-risk collision excitation graph; no matter how the space environment disturbs the rendezvous event, it is still safe;

[0087] If the adjustment coefficient α is 10 -0.6 ~10 0.6 When the range changes, the collision probability Pc changes very little (<1×10 -5), are insensitive to space weather variations, so the rendezvous risk is not affected by the development of solar storms;

[0088] The collision probability Pc varies greatly with the adjustment coefficient α (>5×10 -5 ), and the reachable domain exceeds the set collision avoidance threshold, the incentive graph is classified as a high-risk incentive graph for collision, and the emergency plan needs to be activated;

[0089] The above process is repeated for each intersection target, and the classification results are sorted out for evaluation and decision-making by the user terminal.

[0090] In other orbit-related matters such as space target re-entry, orbital lifetime estimation, and fuel budget, repeat steps 1) to 3) to obtain the space environment stimulus atlas of orbit-related matters in the corresponding scenario, classify them accordingly, obtain the corresponding classification results, and then organize them accordingly for user terminal decision-making.

[0091] Example 1.

[0092] like Figure 1 As shown, the present invention provides a space environment incentive graph evaluation method for spacecraft orbit-related matters, the method comprising:

[0093] Based on the acquired orbital and space environment data sets, the orbital positions and velocities of the primary spacecraft and the rendezvous target are extracted, and conventional space debris early warning calculations are performed. Using the pre-set collision distance as the criterion and the rendezvous distance, multiple close-range rendezvous targets are screened and a list of dangerous targets is compiled.

[0094] When performing collision warning calculations on the main spacecraft of satellite number A, it is found that the space debris numbered B has a close and dangerous rendezvous with it. This rendezvous target is an element in the dangerous target list. Based on the aerodynamic adjustment coefficient of a main spacecraft and the start adjustment coefficient of the rendezvous target, the calculated collision probability is 1.44×10 -4 , as shown in Table 1:

[0095] Table 1 Target rendezvous information list

[0096]

[0097] The collision probability is 1.44×10 -4 The collision probability threshold for taking evasive action is exceeded. -4 However, the calculated collision probability is highly uncertain due to errors in atmospheric density and space environment forecasts. This makes it difficult to decide whether to evade the primary spacecraft.

[0098] By using the space environment excitation diagram method, the aerodynamic adjustment coefficient α of the two rendezvous targets (main spacecraft and space debris) is changed bidirectionally to cover all aerodynamic uncertainties and give a collision probability distribution diagram under various uncertainties. For the above specific experimental environment, for the rendezvous target, the aerodynamic adjustment coefficient of the main spacecraft is used as the horizontal coordinate, and the aerodynamic adjustment coefficient and collision probability of the rendezvous target are used as the vertical coordinate to draw the space environment excitation diagram of the space debris collision risk, and the reachable domain is marked on the space environment excitation diagram, as shown in the figure below. Figure 1 As shown. It can be seen that the collision probability is 8×10 -5 ~1.5×10 -4 The range of variation is: 1.2×10 -4 ~1.3×10 -4 That is to say, no matter how the space environment changes, the collision probability of this close encounter event is always greater than 1.0×10 -4 This is a high-risk collision incentive diagram, and the emergency plan needs to be activated to maneuver the main spacecraft to avoid collision.

[0099] Example 2.

[0100] The present invention also provides a space environment incentive map evaluation system for spacecraft orbit-related matters, the system comprising: a data acquisition module, a target list acquisition module and an incentive map drawing module;

[0101] The data acquisition module is used to obtain orbit and space environment data sets in the space debris early warning mission;

[0102] The target list acquisition module is used to extract the orbital position and velocity of the main spacecraft and the rendezvous target from the acquired orbital and space environment data sets, perform conventional space debris early warning calculations, and use the pre-set collision distance as a criterion and the rendezvous distance as the rendezvous distance to screen out multiple close-range rendezvous targets to form a dangerous target list;

[0103] The excitation map drawing module is used to draw a space environment excitation map of space debris collision risk for each rendezvous target in the dangerous target list, using the main spacecraft aerodynamic adjustment coefficient as the horizontal coordinate and the aerodynamic adjustment coefficient of the rendezvous target as the vertical coordinate, with the color bar representing the collision probability value, and draw a reachable domain on the space environment excitation map;

[0104] Repeat the process of the excitation map drawing module to obtain the space environment excitation map for each intersection target, obtain the space environment excitation map set, classify it, obtain the classification results, and then organize them for user terminal evaluation and decision-making.

[0105] Finally, it should be noted that the above embodiments are intended only to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions to the technical solutions of the present invention do not depart from the spirit and scope of the technical solutions of the present invention and are intended to be encompassed by the claims of the present invention.

Claims

1. A space environment incentive graph evaluation method for spacecraft orbit-related matters, the method comprising: Step 1) In the space debris early warning mission, obtain orbital and space environment datasets; Step 2) Extract the orbital positions and velocities of the primary spacecraft and the rendezvous target from the acquired orbital and space environment datasets, perform conventional space debris early warning calculations, and use a pre-set rendezvous distance threshold criterion to screen out multiple close rendezvous targets to form a list of dangerous targets; Step 3) according to the orbital atmospheric density of the host spacecraft and the ballistic coefficient of the host spacecraft, multiply and couple them in the drag equation; Among them, F d1 The aerodynamic force of the main spacecraft; ρ1 is the orbital atmospheric density of the main spacecraft; BC1 is the ballistic coefficient of the main spacecraft; v r is the relative atmospheric speed of the rendezvous target; According to the main spacecraft aerodynamic adjustment coefficient α1, the collision probability Pc1 of the main spacecraft is calculated; Pc1=f(α1×F d1 ) By adjusting the main spacecraft aerodynamic adjustment coefficient α1, the main spacecraft aerodynamic force F is adjusted bidirectionally. d1 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas; According to the orbital atmospheric density of the rendezvous target and the ballistic coefficient of the rendezvous target, they are multiplied and coupled in the drag equation; Among them, F d2 is the aerodynamic force of the rendezvous target; ρ2 is the orbital atmospheric density of the rendezvous target; BC2 is the ballistic coefficient of the rendezvous target; v r is the relative atmospheric speed of the rendezvous target; According to the aerodynamic adjustment coefficient α2 of the rendezvous target, the collision probability Pc2 of the rendezvous target is calculated; Pc2=f(α2×F d2 ) By adjusting the aerodynamic adjustment coefficient α2 of the rendezvous target, the aerodynamic force F of the rendezvous target is adjusted in both directions. d2 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas; Thus, for each rendezvous target, a space environment excitation map of the space debris collision risk is drawn, with the main spacecraft aerodynamic adjustment coefficient as the horizontal axis and the aerodynamic adjustment coefficient and collision probability of the rendezvous target as the vertical axis. In the drawn space environment excitation map, an interval range is formed from the collision probability minimum area to the collision probability maximum area; and based on the upper and lower limits of the space environment forecast, a reachable domain is drawn on the space environment excitation map; Step 4) Repeat step 3) above to obtain a spatial environment stimulus atlas, classify it, obtain classification results, and then organize them for user terminal evaluation and decision-making.

2. The space environment incentive graph evaluation method for spacecraft orbit-related matters according to claim 1 is characterized in that: The orbital and space environment data set includes but is not limited to: the orbital position, velocity and space environment Kp and F10.7 index of the main spacecraft and the rendezvous target; wherein the rendezvous target is background space debris.

3. The space environment incentive graph evaluation method for spacecraft orbit-related matters according to claim 1 is characterized in that: The step 2) specifically includes: From the acquired orbital and space environment data sets, the orbital positions and velocities of the main spacecraft and the rendezvous target are extracted to perform conventional space debris early warning calculations: During the warning time ΔT set by the user, a rough screening is performed using the orbital altitudes of the main spacecraft and background space debris; The orbital altitude of the main spacecraft is within the range of ±Δh. It is determined whether the orbit of the main spacecraft intersects with the orbit of the background debris. If there is an intersection between the main spacecraft and the rendezvous target, the background space debris is retained and used as a rough rendezvous target and stored in the coarse screening target list; If there is no intersection between the main spacecraft and the rendezvous target, the background space debris is eliminated; Within ΔT, the orbital position of the main spacecraft and each coarse-screened target in the coarse-screened target list is determined with a step size of s. According to the orbital position and speed of the two, the intersection distance between the main spacecraft and each coarse-screened target is determined, and the closest intersection distance set between the main spacecraft and each coarse-screened target is formed. Where i = 1, 2…n; The intersection distance threshold r is set in advance thresh As the criterion, it is determined whether each value in the nearest intersection distance set is less than the preset intersection distance threshold r thresh ; If the i-th intersection distance Less than r thresh , it will be regarded as a space target and stored in the dangerous target list; If the i-th intersection distance Greater than or equal to r thresh , delete it.

4. The space environment incentive graph evaluation method for spacecraft orbit-related matters according to claim 1 is characterized in that: The step 4) specifically includes: For the space environment excitation diagram of the i-th rendezvous target, the Pc value calculated when α1 = 0, α2 = 0 is used as the current collision probability value; where α1 is the aerodynamic adjustment coefficient of the main spacecraft and α2 is the aerodynamic adjustment coefficient of the rendezvous target; If the current collision probability value is in the Pc maximum value area, the incentive graph is classified as a low-collision risk incentive graph; If the current collision probability value is in the Pc minimum area, the incentive graph is classified as a low-collision risk incentive graph; If both adjustment coefficients are between 10 -0.6 ~10 0.6 When the range changes, the collision probability is <1×10 -5 , is not sensitive to space weather changes, and the rendezvous risk is not affected by the development of solar storms; Collision probability Pc>5×10 -5 , and the reachable domain exceeds the set collision avoidance threshold, the incentive graph is classified as a high-risk incentive graph for collision, and the emergency plan needs to be activated; The above process is repeated for each intersection target, and the classification results are sorted out for evaluation and decision-making by the user terminal.

5. A space environment incentive graph evaluation system for spacecraft orbit-related matters, characterized in that: The system includes: a data acquisition module, a target list acquisition module and an incentive graph drawing module; The data acquisition module is used to obtain orbit and space environment data sets in the space debris early warning mission; The target list acquisition module is used to extract the orbital position and velocity of the main spacecraft and the rendezvous target from the acquired orbital and space environment data sets, perform conventional space debris early warning calculations, and use the pre-set collision distance as a criterion and the rendezvous distance as the rendezvous distance to screen out multiple close-range rendezvous targets to form a dangerous target list; The excitation map drawing module is used to multiply and couple in the drag equation according to the orbital atmospheric density of the main spacecraft and the ballistic coefficient of the main spacecraft; Among them, F d1 The aerodynamic force of the main spacecraft; ρ1 is the orbital atmospheric density of the main spacecraft; BC1 is the ballistic coefficient of the main spacecraft; v r is the relative atmospheric speed of the rendezvous target; According to the main spacecraft aerodynamic adjustment coefficient α1, the collision probability Pc1 of the main spacecraft is calculated; Pc1=f(α1×F d1 ) By adjusting the main spacecraft aerodynamic adjustment coefficient α1, the main spacecraft aerodynamic force F is adjusted bidirectionally. d1 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas; According to the orbital atmospheric density of the rendezvous target and the ballistic coefficient of the rendezvous target, they are multiplied and coupled in the drag equation; Among them, F d2 is the aerodynamic force of the rendezvous target; ρ2 is the orbital atmospheric density of the rendezvous target; BC2 is the ballistic coefficient of the rendezvous target; v r is the relative atmospheric speed of the rendezvous target; According to the aerodynamic adjustment coefficient α2 of the rendezvous target, the collision probability Pc2 of the rendezvous target is calculated; Pc2=f(α2×F d2 ) By adjusting the aerodynamic adjustment coefficient α2 of the rendezvous target, the aerodynamic force F of the rendezvous target is adjusted in both directions. d2 ,grid calculation of the corresponding collision probability, and then forming different collision risk areas; Thus, for each rendezvous target, a space environment excitation map of the space debris collision risk is drawn, with the main spacecraft aerodynamic adjustment coefficient as the horizontal axis and the aerodynamic adjustment coefficient and collision probability of the rendezvous target as the vertical axis. In the drawn space environment excitation map, an interval range is formed from the collision probability minimum area to the collision probability maximum area; and based on the upper and lower limits of the space environment forecast, a reachable domain is drawn on the space environment excitation map; Repeat the process of the incentive map drawing module to obtain the spatial environment incentive map set, classify it, obtain the classification results, and then organize them for user terminal evaluation and decision-making.

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