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

Abstract

The invention relates to a same-orbit multi-target foundation measurement and control boundary condition calculation method. The method comprises the following steps: calculating the half-power beam width of measurement and control equipment; calculating the maximum distance between the main target and the measurement and control equipment in the measurement and control process; calculating the maximum allowable attenuation value of the measurement and control link according to the measurement and control link budget margin and the measurement and control link allowable minimum margin; calculating the actual device-ground distance between the measurement and control equipment and the main target, the corrected measurement and control link maximum allowable attenuation value and the corresponding measurement and control equipment antenna elevation angle deviation; calculating measurement and control boundary conditions; and normalizing the obtained measurement and control boundary condition to the in-orbit space target distance of the main target. According to the method, the multi-target foundation measurement and control boundary condition calculation is completed through the antenna pointing deviation gain difference value of the foundation measurement and control equipment by combining the main target measurement and control antenna gain, the spatial position geometrical relationship of the main target and the foundation measurement and control equipment and the wireless signal spatial transmission characteristics, 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 field of spacecraft parallel measurement and control technology, and in particular to a method for calculating boundary conditions of ground-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 measurement and control equipment beam is pointed at the main target. Using the characteristic that 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 measurement and control equipment 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 conditions based on the half-power beam of the measurement and control equipment are 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 measurement and control equipment in the measurement 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 measurement and control link margin. Taking the satellite at an orbital altitude of 600km as an example, the difference in the ground measurement and control link margin can reach 10dB when entering and leaving the measurement and control area and when the satellite passes overhead. In addition, the change in the spatial distance relationship between the main target, boundary and measurement and control equipment will also bring about the link margin difference. The boundary calculation does not take the link margin change into account. Summary of the invention

[0007] 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 ground-based measurement and control of multiple targets on the same orbit, which can be applicable to spacecraft of any orbital altitude and any residual measurement and control link.

[0008] To achieve the above-mentioned object of the invention, the present invention provides a method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track, comprising the following steps:

[0009] Step S1, calculating the half-power beam width of the measurement and control equipment;

[0010] Step S2, calculating the maximum distance between the main target and the measurement and control equipment during the measurement and control process;

[0011] 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;

[0012] Step S4, calculating the actual distance between the measurement and control device and the main target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control device antenna elevation angle deviation according to the measurement and control device antenna elevation angle when the measurement and control device points to the main target;

[0013] Step S5, calculating the measurement and control boundary conditions according to the actual distance between the main target and the measurement and control equipment, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control equipment antenna elevation deviation;

[0014] Step S6: normalize the calculated measurement and control boundary conditions to the spatial target distance within the orbit of the main target.

[0015] According to a technical solution of the present invention, it also includes:

[0016] Step S7, starting from the lowest elevation angle of the measurement and control equipment, increase the elevation angle of the measurement and control equipment antenna according to a fixed step size, and repeat steps S4 to S6 according to each increase of the measurement and control equipment antenna elevation angle until the measurement and control equipment antenna elevation angle reaches the highest elevation angle of the measurement and control equipment.

[0017] According to a technical solution of the present invention, the half-power beam width HPBW of the measurement and control equipment is described by the beam angle, and its calculation formula is:

[0018]

[0019] Among them, c is the speed of light, λ is the wavelength of the measurement and control signal, D is the antenna diameter, and f is the measurement and control radio signal frequency.

[0020] According to a technical solution of the present invention, define α G is the angle between the connecting line between the main target and the measurement and control equipment and the vertical line of the flight direction of the main target, R G is the distance between the main target and the measurement and control equipment, and its calculation formula is as follows:

[0021]

[0022] Among them, Re is the average radius of the earth, h is the orbital height of the main target, E G is the elevation angle of the measurement and control equipment antenna.

[0023] 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:

[0024] ΔM=MM min (4)

[0025] Where M is the budget margin of the measurement and control link, M min Allowing minimum margin for the TT&C link;

[0026] The calculation formula of the measurement and control equipment antenna angle deviation θ corresponding to the maximum allowable attenuation value ΔM of the measurement and control link is as follows:

[0027]

[0028] According to a technical solution of the present invention, in step S2, the maximum distance between the measurement and control device and the main target during the measurement and control process is calculated according to the lowest elevation angle allowed by the measurement and control device.

[0029] According to a technical solution of the present invention, the maximum allowable attenuation value of the measurement and control link after correction is defined as ΔM′, and the angle deviation of the measurement and control equipment antenna is θ′. The calculation formula of the maximum allowable attenuation value ΔM′ of the measurement and control link after correction is:

[0030] ΔM′=ΔM+20log(R Gmax )-20log(R) (7)

[0031] Where R represents the actual distance between the main target and the measurement and control equipment during measurement and control, R Gmax Indicates the maximum distance between the measurement and control equipment and the main target.

[0032] According to a technical solution of the present invention, in step S5, it specifically includes:

[0033] For the two front and rear boundaries θ1 and θ2 of the main target's flight direction, take θ′ as the initial value. According to the geometric relationship between the measurement and control equipment and the main target, the front boundary of the main target before passing the top corresponds to the measurement and control equipment antenna elevation angle E. G +θ1, the front boundary of the main target after passing the top corresponds to the elevation angle of the measurement and control equipment antenna E G -θ1, calculate the distance R1 between the device and the ground when the main target is located at the front boundary, calculate the maximum allowable attenuation value ΔM1′ of the measurement and control link after correction when the main target is located at the front boundary, and converge θ1 through bisection iteration in the range of [0.5×θ1,1.5×θ1] until the following formula (8) is established;

[0034] According to the rear boundary of the main target before passing the top, the corresponding measurement and control equipment antenna elevation angle is E G -θ2, the elevation angle of the measurement and control equipment antenna corresponding to the rear boundary of the main target after passing the top is E G +θ2, calculate the distance R2 between the device and the ground when the main target is located at the rear boundary, calculate the maximum allowable attenuation value ΔM2′ of the measurement and control link after correction when the main target is located at the rear boundary, and converge θ2 through bisection iteration in the range of [0.5×θ2,1.5×θ2] until the following formula (9) is established;

[0035]

[0036] Among them, ε is the allowable numerical deviation.

[0037] 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:

[0038]

[0039] Compared with the prior art, the present invention has the following beneficial effects:

[0040] The present invention combines the gain of the spacecraft measurement and control antenna, the spatial position geometric relationship between the spacecraft and the ground measurement and control equipment, and the spatial transmission characteristics of the wireless signal, and forms a multi-target ground-based measurement and control boundary condition calculation method and process by calculating the difference in gain of the measurement and control equipment antenna pointing deviation and correcting the difference in space transmission link loss. Compared with the traditional method of calculating the boundary with the half-power beam of the measurement and control equipment antenna, the present invention can be applied to spacecraft of any orbital altitude and any margin measurement and control link.

[0041] 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 measurement and control equipment, and the boundary is located outside the spacecraft orbit, resulting in poor measurement and control targeting.

[0042] 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

[0043] 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.

[0044] Figure 1 A flowchart schematically shows a method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track according to one embodiment of the present invention;

[0045] Figure 2 Schematic diagram showing the boundaries of traditional measurement and control methods;

[0046] Figure 3 A schematic diagram schematically shows the relationship between the distance angle between the main target and the measurement and control equipment according to an embodiment of the present invention;

[0047] Figure 4 Schematically showing a schematic diagram of a measurement and control boundary according to an embodiment of the present invention;

[0048] Figure 5 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

[0049] 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.

[0050] 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.

[0051] like Figure 1 As shown, a method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track of the present invention comprises the following steps:

[0052] Step S1, calculating the half-power beam width of the measurement and control equipment;

[0053] Step S2, calculating the maximum distance between the main target and the measurement and control equipment during the measurement and control process;

[0054] 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;

[0055] Step S4, calculating the actual distance between the measurement and control device and the main target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control device antenna elevation angle deviation according to the measurement and control device antenna elevation angle when the measurement and control device points to the main target;

[0056] Step S5, calculating the measurement and control boundary conditions according to the actual distance between the main target and the measurement and control equipment, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control equipment antenna elevation deviation;

[0057] Step S6: normalize the calculated measurement and control boundary conditions to the spatial target distance within the orbit of the main target.

[0058] In this embodiment, the spacecraft measurement and control antenna gain, the spatial position geometric relationship between the spacecraft and the measurement and control equipment, and the spatial transmission characteristics of the wireless signal are combined, and the measurement and control equipment antenna pointing deviation gain difference calculation and space transmission link loss difference correction are performed to complete the calculation of multi-target ground-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.

[0059] like Figures 2 to 4 As shown, the following takes the calculation of multi-target ground-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 ground-based measurement and control boundary conditions of multiple targets in the same orbit provided by the present invention.

[0060] Step S1, calculating the half-power beam width of the measurement and control equipment.

[0061] The half-power beam width HPBW of the measurement and control equipment is usually described by the beam angle. The half-power beam width HPBW of the measurement and control equipment is calculated based on the measurement and control frequency of the main target of the spacecraft and the antenna aperture of the measurement and control equipment. The calculation formula of the half-power beam width HPBW of the measurement and control equipment is as follows:

[0062]

[0063] Among them, c is the speed of light, λ is the wavelength of the measurement and control signal, D is the antenna diameter, and f is the measurement and control radio signal frequency.

[0064] Different HPBWs are used for measurement and control links in different frequency bands.

[0065] Define α GThe angle between the connecting line of the main target and the measurement and control equipment and the vertical line of the main target's flight direction, R G The distance between the main target and the measurement and control equipment is calculated as follows:

[0066]

[0067] Among them, R e is the average radius of the Earth, h is the orbital height of the main target, E G is the elevation angle of the measurement and control equipment antenna.

[0068] Step S2: Calculate the maximum distance between the main target and the measurement and control equipment during the measurement and control process.

[0069] E T The value is based on the lowest elevation angle allowed by the measurement and control equipment. According to formulas (2) and (3), the maximum distance between the measurement and control equipment and the main target during the measurement and control process can be calculated: Gmax .

[0070] 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.

[0071] The calculation formula for the maximum allowable attenuation value ΔM of the measurement and control link is as follows:

[0072] ΔM=MM min (4)

[0073] Where M is the budget margin of the measurement and control link, M min Allowing minimum margin for the TT&C link;

[0074] The calculation formula for the measurement and control equipment antenna angle deviation θ corresponding to the maximum allowable attenuation value ΔM of the measurement and control link is as follows:

[0075]

[0076] Therefore, we can know that the calculation formula for calculating ΔM through θ is as follows:

[0077]

[0078] 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.

[0079] The above calculation only considers the gain deviation caused by the antenna pointing of the ground-based measurement and control equipment, 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 measurement and control antenna (pointing to the main target) and the pointing deviation point (pointing to the boundary). It also needs to be corrected based on the boundary conditions of spatial attenuation and pointing deviation.

[0080] Generally, considering the link budget, the distance between the main target and the measurement and control equipment is usually the longest (i.e., R Tmax ), therefore, when the actual distance between the main target and the measurement and control equipment 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:

[0081] ΔM′=ΔM+20log(R Tmax )-20log(R) (7)

[0082] Step S4, according to the elevation angle of the measurement and control device antenna when the measurement and control device points to the main target, calculate the actual distance between the measurement and control device and the main target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control device antenna elevation angle deviation.

[0083] Specifically, when pointing to the main target, the antenna elevation angle of the measurement and control equipment is within the antenna elevation angle range allowed by the measurement and control equipment. For any angle within the antenna elevation angle range allowed by the measurement and control equipment, the actual device-to-ground distance R between the main target and the measurement and control equipment at this time can be calculated by formulas (2) and (3). The corrected maximum allowable attenuation value ΔM′ of the measurement and control link can be calculated based on the actual device-to-ground distance R and formula (7). The corrected maximum allowable attenuation value ΔM′ of the measurement and control link and formula (5) can be used to calculate the antenna angle deviation θ′ of the measurement and control equipment corresponding to the corrected maximum allowable attenuation value ΔM′ of the measurement and control link.

[0084] Step S5, calculating the measurement and control boundary conditions according to the actual distance between the measurement and control equipment and the main target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control equipment antenna angle deviation;

[0085] For the two front and rear boundaries θ1 and θ2 of the main target's flight direction, take θ′ as the initial value. According to the geometric relationship between the ground measurement and control equipment and the main target, the front boundary of the main target before passing the top corresponds to the measurement and control equipment antenna elevation angle E. G +θ1, the front boundary of the main target after passing the top corresponds to the elevation angle of the measurement and control equipment antenna E G -θ1, calculate the distance R1 between the device and the ground when the main target is located at the front boundary, calculate the maximum allowable attenuation value ΔM1′ of the measurement and control link after correction when the main target is located at the front boundary, and converge θ1 through bisection iteration in the range of [0.5×θ1,1.5×θ1] until the following formula (8) is established;

[0086] According to the rear boundary of the main target before passing the top, the corresponding measurement and control equipment antenna elevation angle is E G -θ2, the elevation angle of the measurement and control equipment antenna corresponding to the rear boundary of the main target after passing the top is E G+θ2, calculate the distance R2 between the device and the ground when the main target is located at the rear boundary, calculate the maximum allowable attenuation value ΔM2′ of the measurement and control link after correction when the main target is located at the rear boundary, and converge θ2 through bisection iteration in the range of [0.5×θ2,1.5×θ2] until the following formula (9) is established;

[0087]

[0088] Among them, ε is the allowable numerical deviation.

[0089] Step S6: normalize the calculated measurement and control boundary conditions to the orbital space target distance.

[0090] 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:

[0091]

[0092] Step S7, starting from the lowest elevation angle of the measurement and control equipment, increase the elevation angle of the measurement and control equipment antenna according to a fixed step size, and repeat steps S4 to S6 according to each increase of the measurement and control equipment antenna elevation angle until the measurement and control equipment antenna elevation angle reaches the highest elevation angle of the measurement and control equipment.

[0093] Through the above steps, the measurement and control boundary conditions for the main target within the elevation angle range of the ground measurement and control equipment antenna can be achieved.

[0094] like Figure 5 As shown in the figure, a and b respectively represent the front boundary and the 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 a satellite at an orbital altitude of 600km as an example, when the maximum allowable attenuation value of the measurement and control link is 3dB, the boundary is expanded by an average of about 2.7 times and a maximum of about 3.1 times. As the maximum allowable attenuation value of the measurement and control link increases, 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 3.6 times and a maximum of about 4.3 times.

[0095] 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.

[0096] 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 ground-based measurement and control of multiple targets on the same track, characterized in that: The following steps are involved: Step S1, calculating the half-power beam width of the measurement and control equipment; Step S2, calculating the maximum distance between the main target and the measurement and control equipment 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 distance between the measurement and control device and the main target, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control device antenna elevation angle deviation according to the measurement and control device antenna elevation angle when the measurement and control device points to the main target; Step S5, calculating the measurement and control boundary conditions according to the actual distance between the main target and the measurement and control equipment, the corrected maximum allowable attenuation value of the measurement and control link and its corresponding measurement and control equipment antenna elevation deviation; Step S6: normalize the calculated measurement and control boundary conditions to the spatial target distance within the orbit of the main target.

2. The method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track according to claim 1 is characterized in that: Also includes: Step S7, starting from the lowest elevation angle of the measurement and control equipment, increase the elevation angle of the measurement and control equipment antenna according to a fixed step size, and repeat steps S4 to S6 according to each increase of the measurement and control equipment antenna elevation angle until the measurement and control equipment antenna elevation angle reaches the highest elevation angle of the measurement and control equipment.

3. The method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track according to claim 1, characterized in that: The half-power beam width HPBW of the measurement and control equipment is described by the beam angle, and its calculation formula is: Among them, c is the speed of light, λ is the wavelength of the measurement and control signal, D is the antenna diameter, and f is the measurement and control radio signal frequency.

4. The method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track according to claim 2 is characterized in that: Define α G is the angle between the connecting line between the main target and the measurement and control equipment and the vertical line of the flight direction of the main target, R G is the distance between the main target and the measurement and control equipment, 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, E G is the elevation angle of the measurement and control equipment antenna.

5. The method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track according to claim 3 is 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 measurement and control equipment 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 ground-based measurement and control of multiple targets on the same track according to claim 4, characterized in that: In step S2, the maximum distance between the measurement and control equipment and the main target during the measurement and control process is calculated according to the lowest elevation angle allowed by the measurement and control equipment.

7. The method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track according to claim 6, characterized in that: The maximum allowable attenuation value of the measurement and control link after correction is defined as ΔM′, and the angle deviation of the measurement and control equipment antenna is θ′. The calculation formula of the maximum allowable attenuation value ΔM′ after correction is: ΔM′=ΔM+20log(R Gmax )-20log(R) (7) Where R represents the actual distance between the main target and the measurement and control equipment during measurement and control, R Gmax Indicates the maximum distance between the measurement and control equipment and the main target.

8. The method for calculating boundary conditions of ground-based measurement and control of multiple targets on the same track according to claim 7 is characterized in that: In the step S5, it specifically includes: For the two front and rear boundaries θ1 and θ2 of the main target's flight direction, take θ′ as the initial value. According to the geometric relationship between the measurement and control equipment and the main target, the front boundary of the main target before passing the top corresponds to the measurement and control equipment antenna elevation angle E. G +θ1, the front boundary of the main target after passing the top corresponds to the elevation angle of the measurement and control equipment antenna E G -θ1, calculate the distance R1 between the device and the ground when the main target is located at the front boundary, calculate the maximum allowable attenuation value ΔM1′ of the measurement and control link after correction when the main target is located at the front boundary, and converge θ1 through bisection iteration in the range of [0.5×θ1,1.5×θ1] until the following formula (8) is established; According to the rear boundary of the main target before passing the top, the corresponding measurement and control equipment antenna elevation angle is E G -θ2, the elevation angle of the measurement and control equipment antenna corresponding to the rear boundary of the main target after passing the top is E G +θ2, calculate the distance R2 between the device and the ground when the main target is located at the rear boundary, calculate the maximum allowable attenuation value ΔM2′ of the measurement and control link after correction when the main target is located at the rear boundary, and converge θ2 through bisection iteration in the range of [0.5×θ2,1.5×θ2] until the following formula (9) is established; Among them, ε is the allowable numerical deviation.

9. The method for calculating boundary conditions of ground-based measurement and control of multiple targets 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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