A Design Method for Single-Loop Inspection Configuration of High-Earth-Orbit Satellite Regional Protection

Abstract

The present invention discloses a single-loop patrol configuration design method for high-orbit satellite regional protection, comprising the following steps: inputting the number of protected objects, their orbital distribution positions, the escort distance, and the number of patrol satellites in high-orbit satellite regional protection; determining the radius range and phase range of the protected area orbit according to the escort distance, orbital distribution positions, and the number of protected objects, and then calculating the transfer time and velocity increment of the patrol satellites during westward descent and eastward ascent; calculating the transfer time during the eastward drift and westward drift processes of the patrol satellites; calculating the patrol period of the single-loop patrol configuration for high-orbit satellite regional protection, calculating the fuel consumption of each patrol satellite in the single-loop patrol configuration for high-orbit satellite regional protection, and combining the number of patrol satellites and the phase range of the protected area orbit to complete the single-loop patrol configuration for high-orbit satellite regional protection. The present invention provides a fast, efficient, and fuel-saving single-loop patrol configuration design method for high-orbit regional protection.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and particularly to a single-loop inspection configuration design method for high-orbit satellite regional protection. Background Technique

[0002] With the continuous development of space technology, the number of spacecraft launched by countries and institutions around the world is increasing day by day. This means that in the face of limited space orbit resources, the competition for space orbits is becoming increasingly fierce. At the same time, the increase in the number of spacecraft also means that more space debris will be generated, which all increases the on-orbit threats to spacecraft. Especially for high-orbit and high-value satellites already in orbit, they do not have the ability to cope with space threats but their own value is very high. Therefore, it is necessary to use inspection satellites to carry out inspection and protection measures for high-orbit and high-value satellites. However, current domestic and foreign research on inspection configuration design mainly focuses on the inspection configuration design for a single spacecraft. Existing literature has designed a relative motion orbit configuration for long-term fly-around monitoring of non-cooperative targets on an elliptical orbit and proposed a corresponding pulse control strategy for maintaining the fly-around orbit configuration; there is also a cluster control algorithm proposed for the satellite configuration design task, which can ensure that the satellites within the configuration are maintained within a specified distance range considering the constraints of relative distance, fuel, and maneuverability; there are also studies on the orbital design and control problems of long-term fly-around observation of target spacecraft on a non-coplanar elliptical orbit. A long-term fly-around observation orbit is designed considering the safety of the fly-around trajectory and the requirements of the mission relative distance, and a corresponding double-pulse control method is given. However, current research on configuration design mostly focuses on the inspection configuration design problem for a single spacecraft, and the research on the inspection protection configuration design for a large-scale orbit area containing multiple targets is still blank.

[0003] In addition, due to the high cost and difficulty of launching high-orbit satellites, the fuel resources of high-orbit satellites are extremely precious and limited. Summary of the Invention

[0004] The purpose of the present invention is to provide a single-loop inspection configuration design method for high-orbit satellite regional protection, in order to overcome the threat problem of space debris to spacecraft in the prior art and the problem that high-value satellites cannot be better protected. A single-loop inspection configuration design method that is fast, efficient, and fuel-saving is provided.

[0005] To achieve the above purpose, the present invention provides the following technical solutions:

[0006] A single-loop inspection configuration design method for high-orbit satellite regional protection, including the following steps:

[0007] S1: Obtain the number of protected objects, orbital distribution positions, guard distances, and the number of inspection satellites in high-orbit satellite regional protection;

[0008] S2: Determine the radius range and phase range of the orbits in the protection area based on the escort distance, orbital distribution position, and the number of protected objects. Then, calculate the transfer time and velocity increment for the westward descent and eastward ascent of the inspection satellite according to the radius range and phase range of the orbits in the protection area.

[0009] S3: Calculate the transfer time for the eastward drift and westward drift processes of the inspection satellite respectively according to the radius range and phase range of the orbits in the protection area.

[0010] S4: Calculate the inspection period of the single-loop inspection configuration for the high-orbit satellite area protection based on the transfer time of the westward descent and eastward ascent of the inspection satellite obtained in S2 and the transfer time of the eastward drift and westward drift processes of the inspection satellite obtained in S3. Then, calculate the fuel consumption of each inspection satellite in the single-loop inspection configuration for the high-orbit satellite area protection according to the velocity increment calculated in S2. Finally, determine the distribution phase of the inspection satellite group in combination with the number of inspection satellites in S1 and the phase range of the orbits in the protection area in S2, and complete the single-loop inspection configuration for the high-orbit satellite area protection.

[0011] Preferably, the calculation method for the phase range of the orbits in the protection area in S2 is as follows:

[0012]

[0013]

[0014]

[0015] Among them, is the westernmost phase of the orbit in the protection area in the geocentric polar coordinate system, is the easternmost phase of the orbit in the protection area in the geocentric polar coordinate system, r G is the radius of the orbit where the protected objects are distributed, is the phase of the orbit where the protected objects are distributed, Δr H is the escort distance.

[0016] Preferably, the calculation method for the radius range of the orbits in the protection area in S2 is as follows:

[0017]

[0018]

[0019] Among them is the radius range of the orbit in the protection area in the geocentric polar coordinate system, r G is the radius of the orbit where the protected objects are distributed, Δr H is the escort distance.

[0020] Preferably, the transfer time for the westward descent and eastward ascent processes of the inspection satellite in S2 is calculated using the Hohmann transfer formula.

[0021] Preferably, the calculation method of the velocity increment is as follows:

[0022]

[0023]

[0024]

[0025]

[0026] and is the velocity increment for rising eastward twice, and is the velocity increment for descending westward twice, μ is the gravitational constant of the central celestial body, is the semi-major axis of the westward drift orbit, is the semi-major axis of the eastward drift orbit, and a3 is the semi-major axis of the Hohmann transfer.

[0027] Preferably, the transfer times of the inspection satellite during the eastward drift and westward drift processes are calculated separately according to the orbital mechanics formula.

[0028] Preferably, S3 is specifically as follows: First, determine the longitude change of the inspection satellite during the eastward drift and westward drift processes, then determine the change in the phase angle, calculate the orbital angular velocities of the three according to the orbital heights of the inspection satellite during the eastward drift and westward drift and the protected object respectively, then calculate the relative angular velocities of the inspection satellite during the eastward drift and westward drift processes relative to the protected object respectively, and finally calculate the transfer times of the inspection satellite during the eastward drift and westward drift processes respectively in combination with the phase angle ranges of the inspection satellite during the eastward drift and westward drift processes and the relative angular velocities of the inspection satellite during the eastward drift and westward drift processes relative to the protected object.

[0029] Preferably, the calculation formulas for the orbital angular velocities of the inspection satellite during the eastward drift and westward drift and the protected object are:

[0030]

[0031]

[0032]

[0033] where r G is the radius of the distributed orbit of the protected object, Δr H is the escort distance, is the orbital angular velocity of the inspection satellite during the eastward drift, is the orbital angular velocity of the inspection satellite during the westward drift, ω G is the orbital angular velocity of the protected object, and μ is the gravitational constant of the central celestial body.

[0034] Preferably, the calculation method for the transfer time in the eastward drift and westward drift processes is as follows:

[0035]

[0036]

[0037] where t E is the eastward drift transfer time of the inspection satellite, t W is the westward drift transfer time of the inspection satellite, is the difference in the change of the phase angle during the eastward drift process of the inspection satellite, is the relative angular velocity of the inspection satellite relative to the protected object during the eastward drift process, is the difference in the change of the phase angle during the westward drift process of the inspection satellite, is the relative angular velocity of the inspection satellite relative to the protected object during the westward drift process.

[0038] Preferably, the inspection period of the single-loop inspection configuration for high-orbit satellite area protection is:

[0039] T c = t WD + t EU + t E + t W

[0040] where T c is the inspection period of the single-loop inspection configuration for high-orbit satellite area protection, t WD is the westward descent transfer time of the protected area orbit, t EU is the eastward ascent transfer time of the protected area orbit.

[0041] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a design method for a single-loop inspection configuration for high-orbit satellite area protection. Based on the natural transfer process and the most fuel-efficient transfer process of eastward drift and westward drift in orbital relative motion, the inspection trajectory and initial configuration of the inspection satellite constellation are designed, and the inspection period and fuel consumption of the designed configuration are analyzed. The fuel is more economical compared to traditional configurations. The present invention provides a fast, efficient, and fuel-saving design method for a single-loop inspection configuration for high-orbit area protection. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 is a flowchart of a design method for a single-loop inspection configuration for high-orbit satellite area protection according to the present invention;

[0043] Figure 2 is a schematic diagram of a single-loop inspection configuration for high-orbit satellite escort according to the present invention;

[0044] Figure 3 is a schematic diagram of the orbit transfer during the eastward ascent process according to the present invention;

[0045] Figure 4 It is a schematic diagram of the geocentric polar coordinate system for the regional protection of high-orbit satellites in the present invention;

[0046] Figure 5 It is a schematic diagram of the regional protection area of high-orbit satellites in the present invention. Specific implementation manners

[0047] The following further elaborates on the present invention in conjunction with specific embodiments, which is an explanation rather than a limitation of the present invention.

[0048] As Figure 1 shown, the present invention is a single-loop patrol configuration design method for the regional protection of high-orbit satellites, including the following steps:

[0049] S1. Input the number n of protected objects, the orbital distribution positions, and the escort distance Δr in the regional protection of high-orbit satellites H , and the number m of patrol satellites;

[0050] S2. Determine the orbital altitude and phase range of the protection area, and calculate the transfer time and the corresponding pulse velocity increment according to the Hohmann transfer formula;

[0051] S3. Calculate the transfer times during the eastward and westward drifts of the orbit respectively according to the orbital dynamics formula;

[0052] S4. Calculate the patrol period and the long-term fuel consumption, and determine the distribution phase of the patrol satellite group in combination with the number of the patrol satellite group;

[0053] The input parameters for the regional protection of high-orbit satellites in step 1 are the number n of protected objects, the orbital phase distribution and the escort distance Δr H , as Figure 4 shown, establish a geocentric polar coordinate system and give the coordinate positions of each spacecraft therein. The polar coordinate has the geocenter as the pole of the polar coordinate system. The protected objects are numbered from west to east according to the phase distribution of the high-orbit satellite protected objects. The westernmost one is numbered 1, and the easternmost one is numbered n. Define the direction of the line connecting the geocenter and the 1st protected object as the polar axis, and the polar axis rotates with the 1st protected object. It is stipulated that the clockwise direction of the angle is positive. Then, the coordinates of the n protected objects in the geocentric polar coordinate system can be written as:

[0054]

[0055] Since the high-orbit protected objects are distributed on the orbit with the same radius r G , so in the formula r G1 = r G2 =... = r Gn = r G

[0056] Step 2: Determine the orbital phase and radius range of the protection area, and calculate the pulse velocity increment and the corresponding transfer time according to the Hohmann transfer formula. A more detailed introduction to this step is as follows:

[0057] Based on the escort distance Δr H Calculate the range of the protection area. First, it is the phase range of the protection area in the geocentric polar coordinate system

[0058]

[0059]

[0060]

[0061] Calculate the orbital radius range of the protection area in the geocentric polar coordinate system

[0062]

[0063]

[0064] As Figure 5 shown, determine that the maneuver starting points for the west descent and east ascent are respectively Next, calculate the transfer time and the corresponding pulse velocity increment for the west descent and east ascent according to the Hohmann transfer formula. The semi-major axes of the circular orbits for the west drift and east drift are respectively Then the semi-major axis a3 of the Hohmann transfer is:

[0065]

[0066] Then the two pulse velocity increments for the east ascent are respectively:

[0067]

[0068]

[0069] In the formula, μ is the gravitational constant of the central celestial body. The gravitational constant of the celestial body with the Earth as the center is:

[0070] μ = 3.986×10 14 m 3 s -2 = 3.986×10 5 km 3 s -2 (10)

[0071] Similarly, the velocity increments of the two pulses for the west descent can be calculated as:

[0072]

[0073]

[0074] Next, calculate the orbital transfer times \(t\) for the westward descent and eastward ascent processes. WD and \(t\) EU

[0075]

[0076] Analyze the change in the maneuver end phase angle for the eastward ascent and westward descent according to the orbital dynamics formula:

[0077]

[0078] As Figure 3 shown, since the transfer time during the Hohmann transfer process is the same as the semi - orbital period of the high orbit \(r\) G where the protected target is located, and the phase transformation is also \(180^{\circ}\), the phase angle of the maneuver end points for the westward descent and eastward ascent in the geocentric polar coordinate system is the same as that of the maneuver start point. Then, as Figure 5 shown, the polar coordinates of the maneuver end points for the westward descent and eastward ascent are

[0079] Step 3: Calculate the transfer times for the eastward and westward orbital drifts respectively according to the orbital dynamics formula, which specifically includes the following steps:

[0080] Determine the longitude change during the eastward and westward drifts. The eastward drift process is from the westward descent end point to the eastward ascent start point. During this period, the orbital radius does not change, and the phase angle change is:

[0081]

[0082] Similarly, the phase angle change for the westward drift process can be obtained as:

[0083]

[0084] Calculate the orbital angular velocities of the three according to the eastward and westward drifts and the orbital altitude of the protected object respectively:

[0085]

[0086]

[0087]

[0088] Calculate the relative angular velocities of the inspection satellite with respect to the protected object during the eastward and westward drifts respectively

[0089]

[0090]

[0091] Calculate the transfer times of the eastward drift and westward drift processes respectively by combining the phase angle ranges of the eastward drift and westward drift processes and the relative angular velocities of the inspection satellite during the eastward drift and westward drift processes with respect to the protected object.

[0092]

[0093]

[0094] Step 4 Calculate the inspection period and fuel consumption, and determine the distribution phase of the inspection satellite group in combination with the number m of the inspection satellite group, which specifically includes the following steps:

[0095] According to the rising-east and falling-west transfer times t WD , t EU calculated in Step 2 and the eastward-drift and westward-drift transfer times t W , t E calculated in Step 3, calculate the inspection period T of the designed single-ring inspection configuration for high-orbit satellite regional protection: c It is:

[0096] T c = t WD + t EU + t E + t W (4)

[0097] During the entire inspection process, no fuel is consumed during the eastward drift and westward drift processes. Therefore, the fuel consumption only includes the rising-east and falling-west processes. According to the Hohmann transfer velocity increment calculated in Step 2, the fuel consumption per single circle of each inspection satellite in the designed single-ring inspection configuration for high-orbit satellite regional protection can be calculated as:

[0098]

[0099] According to the number m of inspection satellites and the phase range of the inspection area carry out the initial configuration design. Distribute p inspection satellites and q inspection satellites evenly according to the phase on the eastward-drift and westward-drift orbits respectively, where m = p + q. The initial polar coordinates of the p inspection satellites on the eastward-drift orbit are where i represents the i-th inspection satellite from west to east on the eastward-drift orbit. Similarly, the initial polar coordinates of the q inspection satellites on the westward-drift orbit are Design the initial phase distribution according to the parity of the number m of inspection satellites.

[0100] When the number m of inspection satellites is even, the number of inspection satellites on the eastward-drift and westward-drift orbits is the same, that is Then the phase angle of the i-th inspection satellite from west to east on the east-drifting orbit is

[0101]

[0102] Since the phase ranges of the east-drifting and west-drifting orbits are the same and the number of inspection satellites is the same, the phase angle distribution of the inspection satellites on the west-drifting orbit is the same as that on the above-mentioned east-drifting orbit. Then the initial polar coordinates of the q inspection satellites on the west-drifting orbit are

[0103] When the number m of inspection satellites is odd, although the phase angle ranges of the east-drifting and west-drifting orbits are the same, due to the longer period of the west-drifting orbit, the number of inspection satellites on the west-drifting orbit in the initial configuration design is pieces, and p = q - 1 pieces are distributed on the east-drifting orbit. According to the uniform distribution of the phase angle, the phase angle of the i-th inspection satellite from west to east on the east-drifting orbit is

[0104]

[0105] The phase angle of the i-th inspection satellite from west to east on the west-drifting orbit is

[0106]

[0107] The following lists a specific embodiment and accompanying drawings to illustrate the specific calculation process of the present invention.

[0108] Embodiment:

[0109] Considering the mission requirement of using 8 inspection satellites to conduct inspection and protection on 13 satellites distributed on a high orbit with an orbital radius of 42164 km, the guard distance is 100 km, and the initial phase of the target satellites is distributed within the longitude range from 75°E to 135°E. Next, the process of designing a single-ring inspection configuration for high-orbit satellite regional protection using the method of the present invention will be listed. The specific steps are as follows:

[0110] S1, input the number n of protected objects, the orbital distribution position, and the guard distance Δr in the high-orbit satellite regional protection H , and the number m of inspection satellites;

[0111] According to the input, determine that the number n of protected objects is 13, the number m of inspection satellites is 8, the guard distance Δr H = 100 km, and the initial orbital phase distribution is at r GOn the orbit of 42,164 km, within the longitude range from 75°E to 135°E, the protected objects are numbered from west to east according to the phase distribution of the high-orbit satellite protected objects. The westernmost is numbered 1 and the easternmost is numbered 13. Taking the earth's center as the pole and the direction of the line connecting the earth's center and the 1st protected object as the polar axis, a polar coordinate system is established, and the clockwise direction is defined as positive. Then the coordinates of the 13 protected objects in the polar coordinate system are written as:

[0112] (42164, 0°), (42164, 5°), (42164, 10°)…(42164, 60°) (1)

[0113] S2, determine the orbital altitude and phase range of the protection area, and calculate the transfer time and the corresponding pulse velocity increment according to the Hohmann transfer formula;

[0114] According to the escort distance Δr H Calculate the regional protection area range. First is the phase range of the protection area in the geocentric polar coordinate system

[0115]

[0116]

[0117]

[0118] Calculate the orbital radius range of the protection area in the geocentric polar coordinate system

[0119]

[0120]

[0121] As Figure 5 shown, determine that the maneuver starting points for westward descent and eastward ascent are (42264, -0.27°) and (42064, 60.27°) respectively. Next, calculate the transfer times and the corresponding pulse velocity increments for westward descent and eastward ascent according to the Hohmann transfer formula. The semi-major axes of the circular orbits for westward drift and eastward drift are Then the semi-major axis a3 of the Hohmann transfer is:

[0122]

[0123] The gravitational constant of the celestial body centered on the earth is given as:

[0124] μ = 3.986×10 14 m 3 s -2 = 3.986×10 5 km3 s -2 (8)

[0125] Then the velocity increments of the two pulses of the eastward rise are respectively:

[0126]

[0127]

[0128] Similarly, the velocity increments of the two pulses of the westward descent can be calculated as:

[0129]

[0130]

[0131] Next, calculate the orbital transfer times t WD 、t EU

[0132]

[0133] According to the orbital dynamics formula, analyze the change of the maneuver end phase angle of the eastward rise and westward descent:

[0134]

[0135] As Figure 3 shown, since the transfer time of the Hohmann transfer process is the same as the semi-orbital period of the high orbit r G where the protection target is located, and the phase transformation is also 180°, so in the geocentric polar coordinate system, the phase angles of the maneuver end points of the westward descent and eastward rise are the same as those of the maneuver start point. Then, as Figure 5 shown, the polar coordinates of the maneuver end points of the westward descent and eastward rise are (42064, -0.27°) and (42264, 60.27°)

[0136] S3. According to the orbital dynamics formula, calculate the transfer times of the orbital eastward drift and westward drift processes respectively. The specific steps are as follows:

[0137] Determine the longitude changes of the eastward drift and westward drift processes. The eastward drift process is from the westward descent end point to the eastward rise start point. During this period, the orbital radius does not change, and the phase angle change is:

[0138]

[0139] Similarly, the phase angle change of the westward drift process can be obtained as:

[0140]

[0141] The orbital angular velocities of the east drift, west drift, and the protected object calculated respectively according to their orbital altitudes:

[0142]

[0143]

[0144]

[0145] Calculate the relative angular velocities of the inspection satellite during the east drift and west drift processes with respect to the protected object respectively

[0146]

[0147]

[0148] Combined with the phase angle ranges during the east drift and west drift processes and the relative angular velocities of the inspection satellite during the east drift and west drift processes with respect to the protected object, calculate the transfer times during the east drift and west drift processes respectively

[0149]

[0150]

[0151] S4. Calculate the inspection period and long-term fuel consumption, and determine the distribution phase of the inspection satellite group in combination with the number of inspection satellites;

[0152] According to the ascending and descending transfer times t WD , t EU calculated in step 2 and the east drift and west drift transfer times t W , t E calculated in step 3, calculate the inspection period T c of the designed single-loop inspection configuration for high-orbit satellite regional protection as:

[0153] T c = t WD + t EU + t E + t W = 11.97 + 11.97 + 1128.13 + 1134.80 = 2286.87h = 95.28day (24)

[0154] During the entire inspection process, no fuel is consumed during the east drift and west drift processes. Therefore, the fuel consumption only includes the ascending and descending processes. According to the Hohmann transfer velocity increment calculated in step 2, the fuel consumption per single loop of each inspection satellite in the designed single-loop inspection configuration for high-orbit satellite regional protection can be calculated as:

[0155]

[0156] Four inspection satellites are evenly distributed according to the phase on the east-drifting and west-drifting orbits respectively, that is, p = q = 4. Then the initial phase distribution of the i-th inspection satellite from west to east on the east-drifting orbit is where the phase angle is

[0157]

[0158] Similarly, the initial phase distribution of the i-th inspection satellite from west to east on the west-drifting orbit is where the phase angle is

[0159]

[0160] Although the embodiments of the present invention have been described above in conjunction with the accompanying drawings, the present invention is not limited to the above specific embodiments and application fields. The above specific embodiments are merely illustrative and guiding, rather than restrictive. Under the inspiration of the specification, those of ordinary skill in the art can also make many forms without departing from the scope protected by the claims of the present invention, and these all fall within the scope of protection of the present invention.

Claims

1. A single-loop inspection configuration design method for high-orbit satellite regional protection, characterized in that It includes the following steps: S1: Obtain the number of protected objects, the orbital distribution positions, the escort distances, and the number of patrolling satellites in the high-orbit satellite area protection; S2: Determine the radius range and phase range of the protection area orbit according to the escort distances, the orbital distribution positions, and the number of protected objects, and then calculate the transfer time and velocity increment of the westward descent and eastward ascent of the patrolling satellites according to the radius range and phase range of the protection area orbit; S3: Calculate the transfer time of the eastward drift and westward drift processes of the patrolling satellites respectively according to the radius range and phase range of the protection area orbit; S4: Calculate the patrol period of the single-loop patrol configuration for high-orbit satellite area protection based on the transfer time of the westward descent and eastward ascent of the patrolling satellites calculated in S2 and the transfer time of the eastward drift and westward drift processes of the patrolling satellites calculated in S3. Then, calculate the fuel consumption of each patrolling satellite in the single-loop patrol configuration for high-orbit satellite area protection according to the velocity increment calculated in S2. Finally, determine the distribution phase of the patrol satellite group in combination with the number of patrolling satellites in S1 and the phase range of the protection area orbit in S2 to complete the single-loop patrol configuration for high-orbit satellite area protection.

2. The single-loop inspection configuration design method for high-orbit satellite regional protection according to claim 1, characterized in that The calculation method for the phase range of the protection area orbit in S2 is as follows: Among them, is the westernmost phase of the protective area orbit in the geocentric polar coordinate system, is the easternmost phase of the protective area orbit in the geocentric polar coordinate system, is the radius of the distribution orbit of the protected object, is the phase of the distribution orbit of the protected object, is the escort distance, is the escort distance corresponding phase angle size.

3. The single-loop patrol configuration design method for high-orbit satellite regional protection according to claim 1, characterized in that The calculation method for the radius range of the protection area orbit in S2 is as follows: wherein is the radius range of the orbit in the geocentric polar coordinate system for the protected area, is the radius of the orbit where the protected objects are distributed, is the escort distance.

4. The single-loop patrol configuration design method for high-orbit satellite regional protection according to claim 1, characterized in that The calculation of the transfer time of the westward descent and eastward ascent processes of the patrolling satellites in S2 is calculated using the Hohmann transfer formula.

5. The single-loop inspection configuration design method for high-orbit satellite regional protection according to claim 4, characterized in that The calculation method for the velocity increment is as follows: and is the velocity increment for two ascensions to the east, and is the velocity increment for two descensions to the west, is the gravitational constant of the central celestial body, is the semi-major axis of the westward drift orbit, is the semi-major axis of the eastward drift orbit, is the semi-major axis of the Hohmann transfer.

6. The single-loop inspection configuration design method for high-orbit satellite regional protection according to claim 1, characterized in that, The transfer time of the eastward drift and westward drift processes of the patrolling satellites is calculated respectively according to the orbital mechanics formula.

7. The single-loop inspection configuration design method for high-orbit satellite regional protection according to claim 1, characterized in that Specifically, S3 is to first determine the longitude change during the eastward drift and westward drift processes of the patrolling satellites, then determine the change in the phase angle, calculate the orbital angular velocities of the three (the patrolling satellites' eastward drift, westward drift, and the protected objects) respectively according to the orbital altitudes of the patrolling satellites' eastward drift, westward drift, and the protected objects, and then calculate the relative angular velocities of the patrolling satellites' eastward drift and westward drift processes with respect to the protected objects respectively. Finally, calculate the transfer time of the eastward drift and westward drift processes of the patrolling satellites respectively in combination with the phase angle range of the patrolling satellites' eastward drift and westward drift processes and the relative angular velocities of the patrolling satellites' eastward drift and westward drift processes with respect to the protected objects.

8. The single-loop inspection configuration design method for high-orbit satellite regional protection according to claim 7, characterized in that The calculation formulas for the orbital angular velocities of the patrolling satellite's eastward drift, westward drift, and the protected object are as follows: Among them, is the radius of the distribution orbit of the protected object, is the escort distance, is the angular velocity of the east-drifting orbit of the inspection satellite, is the angular velocity of the west-drifting orbit of the inspection satellite, is the orbital angular velocity of the protected object, is the gravitational constant of the central celestial body.

9. The single-loop inspection configuration design method for high-orbit satellite regional protection according to claim 7, characterized in that The calculation method for the transfer time of the eastward drift and westward drift processes is as follows: Among them, is the eastward drift transfer time of the inspection satellite, is the westward drift transfer time of the inspection satellite, is the difference in phase angle change during the eastward drift of the inspection satellite, is the relative angular velocity of the inspection satellite with respect to the protected object during the eastward drift, is the difference in phase angle change during the westward drift of the inspection satellite, is the relative angular velocity of the inspection satellite with respect to the protected object during the westward drift.

10. The single-loop patrol configuration design method for high-orbit satellite regional protection according to claim 9, characterized in that, The patrol period of the single-loop patrol configuration for high-orbit satellite area protection is: Among them, is the inspection period of the single-loop inspection configuration for the high-orbit satellite area protection, is the orbital westward descent transfer time of the protection area, is the orbital eastward ascent transfer time of the protection area.

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