Same-orbit multi-target space-based measurement and control boundary condition calculation method

Abstract

The invention relates to a same-orbit multi-target space-based measurement and control boundary condition calculation method. The method comprises the following steps: calculating the half-power beam width of an inter-satellite antenna of relay satellites; calculating the maximum inter-satellite distance between the main target and the relay satellite in the measurement and control process; calculating the maximum allowable attenuation value of the measurement and control link; calculating the actual inter-satellite distance between the relay satellite and the main target, the corrected maximum allowable attenuation value of the measurement and control link and the corresponding inter-satellite antenna angle deviation of the relay satellite; calculating measurement and control boundary conditions; and normalizing the measurement and control boundary condition obtained by calculation to the orbit space target distance. According to the method, the main target measurement and control antenna gain, the spatial position geometrical relationship between the main target and the relay satellites and the wireless signal space transmission characteristics are combined, the multi-target space-based measurement and control boundary condition calculation is completed through the inter-satellite antenna pointing deviation gain difference value of the relay satellites, and the method can be suitable for any orbit height main target and any margin measurement and control link.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft parallel measurement and control, and in particular to a method for calculating boundary conditions of space-based measurement and control of multiple targets on the same orbit. Background Art

[0002] There are scenarios in aerospace activities where parallel measurement and control is provided for multiple spacecraft, such as the rendezvous and docking and separation and evacuation of spacecraft and space station, the initial stage of launch vehicle active phase and spacecraft orbital entry, and the initial stage of multiple satellites orbital entry. Since the movement directions and speeds of spacecraft or launch vehicles at different locations are different, it is impossible to form stable multi-target measurement and control conditions. Therefore, the current multi-target measurement and control technology is mainly applicable to multiple spacecraft or launch vehicles in the same orbit. When performing multi-target measurement and control, a main target is usually selected, and the intersatellite antenna beam of the relay satellite is pointed at the main target. The gain change of the measurement and control beam within the half-power beam range is no more than 3dB. It is considered that other targets within the half-power beam range of the intersatellite antenna have the basic conditions for parallel measurement and control. Then, electromagnetic compatibility between multiple targets is achieved through multiple multiplexing methods such as frequency division, space division, and code division, and finally multi-target parallel measurement and control is achieved.

[0003] The above multi-target measurement and control method has the following problems in practical application:

[0004] 1. The actual measurement and control link margin of the spacecraft / launch vehicle may be larger or less than 3dB, and the boundary condition based on the half-power beam of the relay satellite intersatellite antenna is inaccurate;

[0005] 2. The boundary condition is usually defined as the spatial distance between the main target and other targets, that is, a circle with the main target as the center, the spatial distance as the radius, and perpendicular to the connection line between the main target and the measurement and control equipment. The orbital characteristics of the spacecraft are not considered, that is, the orbit of the spacecraft is not located within the above circle, and the boundary definition is not rigorous;

[0006] 3. The spatial distance between the spacecraft and the relay satellite in the relay tracking and control area changes from far to near and then from near to far. The change in spatial distance brings about the change in the tracking and control link margin. Taking the satellite at an orbital altitude of 600km as an example, the link margin change in the relay tracking and control area can reach 1.5dB; in addition, the change in the spatial distance relationship between the main target, the boundary and the relay satellite will also bring about the link margin difference. The boundary calculation does not take the link margin change into account.

[0007] Therefore, in aerospace activities such as rendezvous and docking, separation and evacuation, and spacecraft launch into orbit, there are scenarios where parallel measurement and control are provided for multiple spacecraft. The traditional calculation method uses the half-power beam of the relay satellite's intersatellite antenna as the boundary, and does not consider the changes in link margin caused by changes in spatial distance. It still needs to be improved in terms of universality, pertinence, and accuracy. Summary of the invention

[0008] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a method for calculating the boundary conditions of multi-target space-based measurement and control in the same orbit, which can be applicable to spacecraft of any orbital altitude and any residual measurement and control link.

[0009] To achieve the above-mentioned object of the invention, the present invention provides a method for calculating boundary conditions of multi-target space-based measurement and control on the same orbit, comprising the following steps:

[0010] Step S1, calculating the half-power beam width of the relay satellite intersatellite antenna;

[0011] Step S2, calculating the maximum inter-satellite distance between the main target and the relay satellite during the measurement and control process;

[0012] Step S3, calculating the maximum allowable attenuation value of the measurement and control link according to the measurement and control link budget margin and the minimum allowable margin of the measurement and control link;

[0013] Step S4, calculating the actual inter-satellite distance between the relay satellite and the primary target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding angle deviation of the inter-satellite antenna of the relay satellite according to the rotation angle of the inter-satellite antenna of the relay satellite when pointing to the primary target;

[0014] Step S5, calculating the measurement and control boundary conditions according to the actual inter-satellite distance between the relay satellite and the primary target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding relay satellite inter-satellite antenna angle deviation;

[0015] Step S6: normalize the calculated measurement and control boundary conditions to the orbital space target distance.

[0016] According to a technical solution of the present invention, it also includes:

[0017] Step S7, starting from the maximum negative rotation angle of the relay satellite intersatellite antenna, the intersatellite antenna rotation angle is increased in sequence according to a fixed step size, and steps S4 to S6 are repeated according to each increase in the intersatellite antenna rotation angle until the intersatellite antenna rotation angle reaches the maximum positive rotation angle.

[0018] According to a technical solution of the present invention, the half-power beam width HPBW of the relay satellite intersatellite antenna is described by the beam angle, and its calculation formula is:

[0019]

[0020] Where c is the speed of light, λ is the wavelength of the relay measurement and control signal, D is the antenna diameter, and f is the frequency of the relay measurement and control link.

[0021] According to a technical solution of the present invention, define α T is the angle between the connecting line between the main target and the relay satellite and the vertical line of the main target flight direction, RT is the inter-satellite distance between the main target and the relay satellite, and its calculation formula is as follows:

[0022]

[0023] Among them, R e is the average radius of the earth, h is the orbital height of the main target, H is the orbital height of the relay satellite, and E T is the rotation angle of the relay satellite intersatellite antenna.

[0024] According to a technical solution of the present invention, in step S3, the calculation formula of the maximum allowable attenuation value ΔM of the measurement and control link is as follows:

[0025] ΔM=MM min (4)

[0026] Where M is the budget margin of the measurement and control link, M min Allowing minimum margin for the TT&C link;

[0027] The calculation formula of the relay satellite inter-satellite antenna angle deviation θ corresponding to the maximum allowable attenuation value ΔM of the measurement and control link is as follows:

[0028]

[0029] According to a technical solution of the present invention, in step S2, the maximum inter-satellite distance between the relay satellite and the main target during the measurement and control process is calculated by taking the relay satellite inter-satellite antenna rotation angle corresponding to when the connecting line between the relay satellite and the main target is tangent to the main target orbit as the maximum rotation angle required for the measurement and control of the main target.

[0030] According to a technical solution of the present invention, the maximum allowable attenuation value of the corrected measurement and control link is defined as ΔM′, where the angle deviation of the relay satellite inter-satellite antenna is θ′, and the calculation formula of the maximum allowable attenuation value ΔM′ of the corrected measurement and control link is:

[0031] ΔM′=ΔM+20log(R Tmax )-20log(R) (7)

[0032] Among them, R represents the actual inter-satellite distance between the main target and the relay satellite during measurement and control, R Tmax Indicates the maximum inter-satellite distance between the primary target and the relay satellite.

[0033] According to a technical solution of the present invention, in step S5, it specifically includes:

[0034] For the front and rear boundaries θ1 and θ2 of the main target flight direction, θ′ is taken as the initial value. According to the geometric relationship between the relay satellite and the main target, the front boundary corresponds to the rotation angle of the relay satellite intersatellite antenna E.T +θ1, when the main target is located at the front boundary, the inter-satellite distance between the main target and the relay satellite is R1, and when the main target is located at the front boundary, the maximum allowable attenuation value of the measurement and control link after correction is ΔM1′.

[0035] In the range of [0.5×θ1,1.5×θ1], converge θ1 through bisection iteration until the following equation (8) holds;

[0036] The rotation angle of the relay satellite intersatellite antenna corresponding to the rear boundary is E T -θ2, when the main target is located at the front boundary, the inter-satellite distance between the main target and the relay satellite is R2, when the main target is located at the rear boundary, the corrected maximum allowable attenuation value of the tracking and control link is ΔM2′, in the range of [0.5×θ2,1.5×θ2], the binary search method is used to iterate and converge θ2 until the following formula (9) is established;

[0037]

[0038] Among them, ε is the allowable numerical deviation.

[0039] According to a technical solution of the present invention, in step S6, the space target distance in the front boundary track and the space target distance in the front boundary track in the flight direction are D1 and D2 respectively, and the calculation formula is as follows:

[0040]

[0041] Compared with the prior art, the present invention has the following beneficial effects:

[0042] The present invention combines the gain of the spacecraft measurement and control antenna, the geometric relationship between the spacecraft and the relay satellite, and the spatial transmission characteristics of the wireless signal, and forms a multi-target space-based measurement and control boundary condition calculation method and process by calculating the difference in the gain of the relay satellite inter-satellite antenna pointing deviation and correcting the difference in the space transmission link loss. Compared with the traditional method of calculating the boundary with the half-power beam of the relay satellite inter-satellite antenna, the present invention can be applied to spacecraft of any orbital altitude and any margin measurement and control link.

[0043] At the same time, the present invention also normalizes the boundary conditions to the distance of the space target in the orbit, solving the problem that the boundary conditions of the traditional method are usually defined as a circle centered on the main target and perpendicular to the connection line between the main target and the relay satellite, avoiding the problem that the boundary is outside the spacecraft orbit, resulting in poor measurement and control targeting.

[0044] The present invention amends the boundary calculation formula based on spatial attenuation and pointing deviation, takes into account the change in the measurement and control link margin caused by the change in spatial distance, and improves the accuracy of boundary calculation. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0046] Figure 1 A flowchart of a method for calculating boundary conditions of multi-target space-based measurement and control on the same track provided in accordance with one embodiment of the present invention is schematically shown;

[0047] Figure 2 Schematic diagram showing the boundaries of traditional measurement and control methods;

[0048] Figure 3 A schematic diagram schematically shows the relationship between the distance angle between the main target and the relay satellite according to an embodiment of the present invention;

[0049] Figure 4 A schematic diagram schematically shows the maximum distance between a main target and a relay satellite according to an embodiment of the present invention;

[0050] Figure 5 Schematically showing a schematic diagram of a measurement and control boundary according to an embodiment of the present invention;

[0051] Figure 6 The schematic diagram shows the improvement in efficiency of the boundary calculation method provided according to an embodiment of the present invention compared with the traditional boundary calculation method. DETAILED DESCRIPTION

[0052] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0053] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0054] like Figure 1 As shown, a method for calculating boundary conditions of multi-target space-based measurement and control on the same track of the present invention comprises the following steps:

[0055] Step S1, calculating the half-power beam width of the relay satellite intersatellite antenna;

[0056] Step S2, calculating the maximum inter-satellite distance between the main target and the relay satellite during the measurement and control process;

[0057] Step S3, calculating the maximum allowable attenuation value of the measurement and control link according to the measurement and control link budget margin and the minimum allowable margin of the measurement and control link;

[0058] Step S4, calculating the actual inter-satellite distance between the relay satellite and the primary target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding angle deviation of the inter-satellite antenna of the relay satellite according to the rotation angle of the inter-satellite antenna of the relay satellite when pointing to the primary target;

[0059] Step S5, calculating the measurement and control boundary conditions according to the actual inter-satellite distance between the relay satellite and the primary target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding relay satellite inter-satellite antenna angle deviation;

[0060] Step S6: normalize the calculated measurement and control boundary conditions to the orbital space target distance.

[0061] In this embodiment, the spacecraft measurement and control antenna gain, the spatial position geometric relationship between the spacecraft and the relay satellite, and the wireless signal space transmission characteristics are combined, and the relay satellite inter-satellite antenna pointing deviation gain difference calculation and space transmission link loss difference correction are used to complete the calculation of multi-target space-based measurement and control boundary conditions. This method fully considers the link margin changes caused by the change in spatial distance and can be applied to spacecraft at any orbital altitude and measurement and control links with any margin. This method further simplifies the use steps of the application scenario by normalizing the boundary conditions to the orbital space target distance, and reduces the calculation difficulty of the measurement and control scenario.

[0062] The following takes the calculation of multi-target space-based measurement and control boundary conditions of a 600km altitude sun-synchronous orbit satellite as an example to describe in detail the method for calculating the boundary conditions of multi-target space-based measurement and control on the same orbit provided by the present invention.

[0063] Step S1, calculating the half-power beam width of the relay satellite intersatellite antenna.

[0064] The half-power beam width HPBW of the relay satellite intersatellite antenna is usually described by the beam angle. The half-power beam width HPBW of the relay satellite intersatellite antenna is calculated based on the spacecraft measurement and control frequency and the aperture of the relay satellite intersatellite antenna. The calculation formula of the half-power beam width HPBW of the relay satellite intersatellite antenna is as follows:

[0065]

[0066] Where c is the speed of light, λ is the wavelength of the relay measurement and control signal, D is the antenna diameter, and f is the frequency of the relay measurement and control link.

[0067] Different HPBWs are used for measurement and control links in different frequency bands.

[0068] Define α T The angle between the line connecting the main target and the relay satellite and the perpendicular to the spacecraft's flight direction, R T is the inter-satellite distance between the spacecraft and the relay satellite, and its calculation formula is as follows:

[0069]

[0070] Among them, R e is the average radius of the earth, h is the orbital height of the spacecraft, H is the orbital height of the relay satellite, and E T is the rotation angle of the relay satellite intersatellite antenna.

[0071] Step S2: Calculate the maximum inter-satellite distance between the main target and the relay satellite during the measurement and control process.

[0072] When the connecting line between the relay satellite and the main target is tangent to the main target orbit, the corresponding rotation angle of the relay satellite intersatellite antenna is the maximum rotation angle required for the main target measurement and control. T The value is the maximum rotation angle required for the main target measurement and control. According to formulas (2) and (3), the maximum inter-satellite distance R between the main target and the relay satellite can be calculated. Tmax .

[0073] Step S3: Calculate the maximum allowable attenuation value of the measurement and control link according to the measurement and control link budget margin and the minimum allowable margin of the measurement and control link.

[0074] The calculation formula for the maximum allowable attenuation value ΔM of the measurement and control link is as follows:

[0075] ΔM=MM min (4)

[0076] Where M is the budget margin of the measurement and control link, M min Allowing minimum margin for the TT&C link;

[0077] The calculation formula of the relay satellite inter-satellite antenna angle deviation θ corresponding to the maximum allowable attenuation value ΔM of the tracking and control link is as follows:

[0078]

[0079] Therefore, we can know that the formula for calculating ΔM through θ is as follows:

[0080]

[0081] In this embodiment, the budget margin of the measurement and control link is 9 dB, and the minimum allowable margin of the measurement and control link during normal operation is 3 dB, so ΔM is 6 dB.

[0082] The above calculation only considers the gain deviation caused by the pointing of the intersatellite antenna of the relay satellite, that is, the maximum allowable attenuation value of the measurement and control link is the difference between the antenna gain at the axial point of the intersatellite antenna (pointing to the main target) and the pointing deviation point (pointing to the boundary), and it also needs to be corrected based on the boundary conditions of spatial attenuation and pointing deviation.

[0083] Generally, considering the link budget, the distance between the spacecraft and the relay satellite is usually the longest (i.e., R Tmax ), therefore, when the actual inter-satellite distance between the main target and the relay satellite is R, since R is less than R Tmax , the corrected maximum allowable attenuation value ΔM′ of the measurement and control link is greater than ΔM. The calculation formula of the corrected maximum allowable attenuation value ΔM′ of the measurement and control link is as follows:

[0084] ΔM′=ΔM+20log(R Tmax )-20log(R) (7)

[0085] Step S4, according to the rotation angle of the relay satellite intersatellite antenna when pointing to the main target, calculate the actual intersatellite distance between the relay satellite and the main target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding relay satellite intersatellite antenna angle deviation.

[0086] Specifically, when pointing to the main target, the rotation angle of the relay satellite intersatellite antenna is within the rotation elevation angle range of the relay satellite intersatellite antenna. For any angle within the rotation elevation angle range of the relay satellite intersatellite antenna, the actual intersatellite distance R between the main target and the relay satellite at this time can be calculated by formulas (2) and (3). According to the actual intersatellite distance R and formula (7), the corrected maximum allowable attenuation value ΔM′ of the measurement and control link can be calculated. According to the corrected maximum allowable attenuation value ΔM′ of the measurement and control link and formula (5), the relay satellite intersatellite antenna angle deviation θ′ corresponding to the corrected maximum allowable attenuation value ΔM′ of the measurement and control link can be calculated.

[0087] Step S5, calculating the measurement and control boundary conditions according to the actual inter-satellite distance between the relay satellite and the primary target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding relay satellite inter-satellite antenna angle deviation;

[0088] For the front and rear boundaries θ1 and θ2 of the main target flight direction, θ′ is taken as the initial value. According to the geometric relationship between the relay satellite and the main target, the front boundary corresponds to the rotation angle of the relay satellite intersatellite antenna E. T +θ1, when the main target is located at the front boundary, the inter-satellite distance between the main target and the relay satellite is R1, and when the main target is located at the front boundary, the maximum allowable attenuation value of the measurement and control link after correction is ΔM1′.

[0089] In the range of [0.5×θ1,1.5×θ1], converge θ1 through bisection iteration until the following equation (8) holds;

[0090] The rotation angle of the relay satellite intersatellite antenna corresponding to the rear boundary is E T -θ2, when the main target is located at the front boundary, the inter-satellite distance between the main target and the relay satellite is R2, when the main target is located at the rear boundary, the corrected maximum allowable attenuation value of the tracking and control link is ΔM2′, in the range of [0.5×θ2,1.5×θ2], the binary search method is used to iterate and converge θ2 until the following formula (9) is established;

[0091]

[0092] Among them, ε is the allowable numerical deviation.

[0093] Step S6: normalize the calculated measurement and control boundary conditions to the orbital space target distance.

[0094] The distance between the space target in the front boundary orbit and the space target in the front boundary orbit in the flight direction are D1 and D2 respectively, and the calculation formula is as follows:

[0095]

[0096] Step S7, starting from the maximum negative rotation angle of the relay satellite intersatellite antenna, the intersatellite antenna rotation angle is increased in sequence according to a fixed step size, and steps S4 to S6 are repeated according to each increase in the intersatellite antenna rotation angle until the intersatellite antenna rotation angle reaches the maximum positive rotation angle.

[0097] Through the above steps, the measurement and control boundary conditions for the main target within the inter-satellite rotation elevation angle range of the relay satellite can be achieved.

[0098] like Figure 6As shown in the figure, a and b respectively represent the front boundary and rear boundary of the flight direction obtained by the calculation method of the present invention, and c represents the measurement and control boundary obtained by the traditional method. The measurement and control boundary conditions calculated by the present invention are effectively expanded, and the multi-target measurement and control capability is further improved. Taking the 600km orbit altitude satellite as an example, for the relay S-band measurement and control link, when the maximum allowable attenuation value of the measurement and control link is 3dB, the boundary is expanded by an average of about 1.6 times and a maximum of about 3.2 times. With the increase of the maximum allowable attenuation value of the measurement and control link, the measurement and control boundary is further expanded. When the maximum allowable attenuation value of the measurement and control link is 9dB, the boundary is expanded by an average of about 2.4 times and a maximum of about 4.1 times; for the relay Ka-band measurement and control link, when the maximum allowable attenuation value of the measurement and control link is 3dB, the boundary is expanded by an average of about 1.7 times and a maximum of about 9.3 times. With the increase of the maximum allowable attenuation value of the measurement and control link, the measurement and control boundary is further expanded. When the maximum allowable attenuation value of the measurement and control link is 9dB, the boundary is expanded by an average of about 2.7 times and a maximum of about 12.7 times.

[0099] In addition, it should be noted that, in this article, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or terminal device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or terminal device. In the absence of further restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, article or terminal device including the elements.

[0100] Finally, it should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, for those skilled in the art, once the basic creative concept of the present invention is known, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A method for calculating boundary conditions of multi-target space-based measurement and control in the same orbit, characterized in that: The following steps are involved: Step S1, calculating the half-power beam width of the relay satellite intersatellite antenna; Step S2, calculating the maximum inter-satellite distance between the main target and the relay satellite during the measurement and control process; Step S3, calculating the maximum allowable attenuation value of the measurement and control link according to the measurement and control link budget margin and the minimum allowable margin of the measurement and control link; Step S4, calculating the actual inter-satellite distance between the relay satellite and the primary target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding angle deviation of the inter-satellite antenna of the relay satellite according to the rotation angle of the inter-satellite antenna of the relay satellite when pointing to the primary target; Step S5, calculating the measurement and control boundary conditions according to the actual inter-satellite distance between the relay satellite and the primary target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding relay satellite inter-satellite antenna angle deviation; Step S6: normalize the calculated measurement and control boundary conditions to the orbital space target distance.

2. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 1, characterized in that: Also includes: Step S7, starting from the maximum negative rotation angle of the relay satellite intersatellite antenna, the intersatellite antenna rotation angle is increased in sequence according to a fixed step size, and steps S4 to S6 are repeated according to each increase in the intersatellite antenna rotation angle until the intersatellite antenna rotation angle reaches the maximum positive rotation angle.

3. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 1, characterized in that: The half-power beam width HPBW of the relay satellite intersatellite antenna is described by the beam angle, and its calculation formula is: Where c is the speed of light, λ is the wavelength of the relay measurement and control signal, D is the antenna diameter, and f is the frequency of the relay measurement and control link.

4. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 3 is characterized in that: Define α T is the angle between the connecting line between the main target and the relay satellite and the vertical line of the main target flight direction, R T is the inter-satellite distance between the main target and the relay satellite, and its calculation formula is as follows: Among them, R e is the average radius of the earth, h is the orbital height of the main target, H is the orbital height of the relay satellite, and E T is the rotation angle of the relay satellite intersatellite antenna.

5. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 3, characterized in that: In step S3, the calculation formula of the maximum allowable attenuation value ΔM of the measurement and control link is as follows: ΔM=MM min (4) Where M is the budget margin of the measurement and control link, M min Allowing minimum margin for the TT&C link; The calculation formula of the relay satellite inter-satellite antenna angle deviation θ corresponding to the maximum allowable attenuation value ΔM of the measurement and control link is as follows:

6. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 5, characterized in that: In step S2, the maximum inter-satellite distance between the relay satellite and the main target during the measurement and control process is calculated by taking the relay satellite inter-satellite antenna rotation angle corresponding to when the connecting line between the relay satellite and the main target is tangent to the main target orbit as the maximum rotation angle required for the measurement and control of the main target.

7. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 6, characterized in that: The maximum allowable attenuation value of the corrected tracking and control link is defined as ΔM′, where the angle deviation of the relay satellite inter-satellite antenna is θ′. The calculation formula for the maximum allowable attenuation value of the corrected tracking and control link ΔM′ is: ΔM′=ΔM+20log(R Tmax )-20log(R) (7) Among them, R represents the actual inter-satellite distance between the main target and the relay satellite during measurement and control, R Tmax Indicates the maximum inter-satellite distance between the primary target and the relay satellite.

8. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 7, characterized in that: In the step S5, it specifically includes: For the front and rear boundaries θ1 and θ2 of the main target flight direction, θ′ is taken as the initial value. According to the geometric relationship between the relay satellite and the main target, the front boundary corresponds to the rotation angle of the relay satellite intersatellite antenna E. T +θ1, when the main target is located at the front boundary, the inter-satellite distance between the main target and the relay satellite is R1, and when the main target is located at the front boundary, the maximum allowable attenuation value of the measurement and control link after correction is ΔM1′. In the range of [0.5×θ1,1.5×θ1], converge θ1 through bisection iteration until the following equation (8) holds; The rotation angle of the relay satellite intersatellite antenna corresponding to the rear boundary is E T -θ2, when the main target is located at the front boundary, the inter-satellite distance between the main target and the relay satellite is R2, when the main target is located at the rear boundary, the corrected maximum allowable attenuation value of the tracking and control link is ΔM2′, in the range of [0.5×θ2,1.5×θ2], the binary search method is used to iterate and converge θ2 until the following formula (9) is established; Among them, ε is the allowable numerical deviation.

9. The method for calculating boundary conditions of multi-target space-based measurement and control on the same track according to claim 8, characterized in that: In step S6, the space target distance in the front boundary track and the space target distance in the front boundary track in the flight direction are D1 and D2 respectively, and the calculation formulas are as follows:

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