Multi-narrow-beam antenna detection control system and strategy

Abstract

The invention discloses a multi-narrow-beam antenna detection control system and strategy used for tracking and capturing a target detection object, and the system comprises an antenna group; the antenna group specifically comprises a main detection antenna and a plurality of auxiliary detection antennas; the main detection antenna forms a main beam detection space at a target detection point; the target detection point is confirmed according to the target expected position of the target detection object; when any antenna in the antenna group detects the target detection object, correcting the target expected position according to the actual position of the target detection object; and the antenna group adjusts the azimuth pitch attitude according to the corrected target expected position. Narrow beams of multiple antennas are superposed to form a cellular wide beam, so that the narrow beam antenna is replaced to track a target with relatively large motion trail distribution, and the risk that a single narrow beam antenna completes capturing and tracking due to an expected position estimation error of the target is avoided.

Description

Technical Field

[0001] The present invention relates to the field of space tracking and detection, and in particular to a multi-narrow beam antenna detection control system and strategy. Background Art

[0002] Regardless of the type of antenna, there is a corresponding spatial range of detection and control. If the path of the target to be tracked is expected to have a low accuracy, once the beam detection space is small, it cannot be quickly captured and tracked. Taking a large low-orbit satellite system as an example, thousands of satellites are launched to form a satellite constellation. In order to improve the launch efficiency of ground rockets, it is often necessary to perform a multi-satellite mission with one rocket. At the moment of separation of the satellite and the rocket, the low-orbit satellite group has not completely dispersed, and the ground tracking and control station antenna needs to quickly capture and track the low-orbit satellite group so that the satellite can adjust its attitude. For the millimeter-wave frequency band large-aperture low-orbit satellite ground tracking and control system, due to the narrow beam width of the single ground antenna, at the moment of separation of the satellite and the rocket, the beam formed in space by the ground station in a program-guided manner may not cover the actual low-orbit satellite group location area, and cannot quickly capture, track and adjust the attitude of the low-orbit satellite at the moment of separation. Summary of the invention

[0003] In order to solve the above technical problem that the detection control range of the antenna in the prior art is not enough to meet the tracking of the target with large expected motion position deviation, the present invention provides a multi-narrow beam antenna detection control system and strategy:

[0004] A multi-narrow beam antenna detection control system for tracking and capturing a target detection object, comprising:

[0005] Antenna group; the antenna group specifically includes a main detection antenna and multiple auxiliary detection antennas;

[0006] The main detection antenna forms a main beam detection space at the target detection point; the plurality of auxiliary detection antennas form a plurality of auxiliary beam detection spaces around the main beam detection space; the auxiliary beam detection space moves along with the movement of the main beam detection space to form a honeycomb beam detection space at the target detection point;

[0007] The target detection point is confirmed according to the target expected position of the target detection object;

[0008] When any one antenna in the antenna group detects a target detection object, the target expected position is corrected according to the actual position of the target detection object;

[0009] The antenna group adjusts the azimuth and pitch attitude according to the corrected expected target position.

[0010] Preferably, it also includes a measurement and control scheduling unit and a measurement and control ground antenna servo feed system, wherein the measurement and control scheduling unit is a ground measurement and control scheduling unit; each of the measurement and control ground antenna servo feed systems corresponds to an antenna in the antenna group;

[0011] The measurement and control scheduling unit generates the expected target position to the measurement and control ground-based antenna feed system, and the measurement and control ground-based antenna feed system controls the antenna to capture, track and adjust the attitude of the target detection object according to the expected target position.

[0012] Preferably, the azimuth and elevation angles of the main detection antenna satisfy:

[0013] (A t1 ,E t1 ),(A t2 ,E t2 ),·……,(A ti ,E ti ),·……;

[0014] The azimuth angles and elevation angles of the multiple auxiliary detection antennas satisfy:

[0015] (A t1 +ΔA 11 ,E t1 +ΔE 11 ),(A t2 +ΔA 12 ,E t2 +ΔE 12 ),·……,(A ti +ΔA 1i ,E ti +ΔE 1i ),·……,(A t1 +ΔA 21 ,E t1 +ΔE 21 ),(A t2 +ΔA 22 ,E t2 +ΔE 22 ),·……,(A ti +ΔA 2i ,E ti +ΔE 2i ),·……,·…,(A t1 +ΔA (n-1)1 ,E t1 +ΔE (n-1)1 ),(A t2 +ΔA (n-1)2 ,E t2 +ΔE (n-1)2 ),·…,(A ti +ΔA (n-1)i ,E ti+ΔE (n-1)i ),·……

[0016] The variable A is the azimuth angle, E is the elevation angle, and (n-1) is the number of auxiliary detection antennas.

[0017] Further preferably, the difference between the azimuth angle and the elevation angle between the main detection antenna and the auxiliary detection antenna satisfies the requirement that the auxiliary beam detection space is superimposed along the periphery of the main beam detection space.

[0018] Further preferably, the relative position between each beam detection space in the honeycomb beam detection space is dynamically fixed.

[0019] Preferably, the target detection object is a target satellite;

[0020] The target detection point is determined according to the ephemeris of the target satellite.

[0021] Preferably, the main beam detection space is circular; the auxiliary beam detection space is circular; the antennas in the antenna group have the same beam width; and the antennas in the antenna group are narrow beam antennas.

[0022] Further preferably, there is an overlapping portion between the auxiliary beam detection space and the main beam detection space, and the overlapping portion divides the circular contour of the main beam detection space equally.

[0023] Further preferably, the number of antennas in the antenna group is 6.

[0024] On the other hand, a multi-narrow beam antenna detection control strategy is provided, which is used to adjust the attitudes of multiple narrow beam antennas to track the satellite when the target low-orbit satellite is separated from the rocket, including:

[0025] The ground measurement and control dispatching unit sends the ephemeris to multiple measurement and control ground servo feed systems;

[0026] The multiple measurement and control ground-based servo-feedback systems adjust the azimuth and elevation attitudes of the narrow beam antennas according to the ephemeris table to form a honeycomb beam detection space at the target detection point;

[0027] When any one of the plurality of measurement and control ground-based servo-feedback systems detects a target low-orbit satellite, the actual position of the target low-orbit satellite is sent to the ground measurement and control scheduling unit;

[0028] The ground measurement and control scheduling unit updates the ephemeris table according to the actual position.

[0029] The present invention includes at least one of the following technical effects: by superimposing the narrow beams of multiple antennas to form a cellular wide beam to replace the narrow beam antenna, it is possible to capture and track aerial targets with large motion trajectory distribution or large expected motion position estimation errors without building new wide beam antennas. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0031] Figure 1 A reference diagram of the use state of a multi-narrow beam antenna detection control system of the present invention, comprising a main antenna 1 and auxiliary antennas 2 to 6 and corresponding main beam detection spaces S1 and auxiliary beam detection spaces S2 to S6;

[0032] Figure 2 A description of the shape of the cellular beam sounding control space of the present invention at different numbers of antennas;

[0033] Figure 3 It is a schematic diagram of the capture efficiency calculation of the present invention;

[0034] Figure 4 A graph showing how the efficiency of a multi-narrow beam antenna detection and control system of the present invention changes as the number of antennas increases;

[0035] Figure 5 The present invention is a flowchart of a multi-narrow beam antenna detection control strategy. DETAILED DESCRIPTION

[0036] In the following description, specific details such as specific system structures, technologies, etc. are provided for the purpose of illustration rather than limitation, so as to provide a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to prevent unnecessary details from obstructing the description of the present application.

[0037] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of the described features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or collections.

[0038] In order to simplify the drawings, only the parts related to the present invention are schematically shown in each figure, and they do not represent the actual structure of the product. In addition, in order to simplify the drawings and facilitate understanding, in some figures, only one of the parts with the same structure or function is schematically drawn or marked. In this article, "one" not only means "only one", but also means "more than one".

[0039] It should be further understood that the term “and / or” used in the specification and appended claims refers to any combination and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0040] In addition, in the description of the present application, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0041] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the specific implementation methods of the present invention will be described below with reference to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings and other implementation methods can be obtained based on these drawings without creative work.

[0042] Embodiment 1:

[0043] like Figure 1 As shown, this embodiment provides a multi-narrow beam antenna detection control system for tracking and capturing a target detection object, comprising: an antenna group; the antenna group specifically comprises a main detection antenna 1 and a plurality of auxiliary detection antennas 2-6; the main detection antenna 1 forms a main beam detection space S1 at a target detection point; the plurality of auxiliary detection antennas 2-6 form a plurality of auxiliary beam detection spaces S2-S6 around the main beam detection space S1; the auxiliary beam detection spaces S2-S6 move along with the movement of the main beam detection space S1 to form a honeycomb beam detection space at the target detection point; the target detection point is confirmed according to the target expected position of the target detection object;

[0044] When any one antenna in the antenna group detects a target detection object, the target expected position is corrected according to the actual position of the target detection object; and the antenna group adjusts the azimuth and pitch attitude according to the corrected target expected position.

[0045] Regardless of the type of antenna, there is a corresponding spatial range of detection and control. If the path of the target to be tracked is expected to have a low accuracy, once the beam detection space is small, it cannot be quickly captured and tracked. Taking a large low-orbit satellite system as an example, thousands of satellites are launched to form a satellite constellation. In order to improve the launch efficiency of ground rockets, it is often necessary to perform a multi-satellite mission with one rocket. At the moment of separation of the satellite and the rocket, the low-orbit satellite group has not completely dispersed, and the ground tracking and control station antenna needs to quickly capture and track the low-orbit satellite group so that the satellite can adjust its attitude. For the millimeter-wave frequency band large-aperture low-orbit satellite ground tracking and control system, due to the narrow beam width of the single ground antenna, at the moment of separation of the satellite and the rocket, the beam formed in space by the ground station in a program-guided manner may not cover the actual low-orbit satellite group location area, and cannot quickly capture, track and adjust the attitude of the low-orbit satellite at the moment of separation.

[0046] Therefore, in the present embodiment, auxiliary beam detection spaces S2 to S6 are formed by auxiliary detection antennas 2 to 6 around the main beam detection space S1 formed by the main detection antenna 1, thereby forming a larger honeycomb beam detection space. The target path is detected through the honeycomb beam detection space, and the expected position is corrected according to the actual position of the detected target object. The actual position is judged according to the expected position to control the posture of the main detection antenna and the auxiliary detection antenna.

[0047] Preferably, it also includes a measurement and control scheduling unit and a measurement and control ground-based servo feed system, wherein the measurement and control scheduling unit is a ground-based measurement and control scheduling unit; each of the measurement and control ground-based servo feed systems corresponds to an antenna in the antenna group; the measurement and control scheduling unit generates the expected target position to the measurement and control ground-based servo feed system, and the measurement and control ground-based servo feed system controls the antenna to perform capture, tracking and attitude adjustment for the target detection object according to the expected target position. The difference between the azimuth angle and the pitch angle between the main detection antenna and the auxiliary detection antenna satisfies the requirement that the auxiliary beam detection space is superimposed along the periphery of the main beam detection space 1. The relative position between each beam detection space in the honeycomb beam detection space is dynamically fixed. The target detection object is a target satellite; the target detection point is determined according to the ephemeris of the target satellite. The main beam detection space S1 is circular; the auxiliary beam detection spaces S2 to S6 are circular; the antennas in the antenna group have the same beam width; and the antennas in the antenna group are narrow beam antennas. There is an overlap between the auxiliary beam detection spaces S2 to S6 and the main beam detection space S1, and the overlap evenly divides the circular contour of the main beam detection space S1. The azimuth and elevation angles of the main detection antenna satisfy:

[0048] (A t1 ,E t1 ),(A t2 ,E t2),·……,(A ti ,E ti ),·……;

[0049] The azimuth angles and elevation angles of the multiple auxiliary detection antennas satisfy:

[0050] (A t1 +ΔA 11 ,E t1 +ΔE 11 ),(A t2 +ΔA 12 ,E t2 +ΔE 12 ),·……,(A ti +ΔA 1i ,E ti +ΔE 1i ),·……,(A t1 +ΔA 21 ,E t1 +ΔE 21 ),(A t2 +ΔA 22 ,E t2 +ΔE 22 ),·……,(A ti +ΔA 2i ,E ti +ΔE 2i ),·……,·……,(A t1 +ΔA (n-1)1 ,E t1 +ΔE (n-1)1 ),(A t2 +ΔA (n-1)2 ,E t2 +ΔE (n-1)2 ),·……,(A ti +ΔA (n-1)i ,E ti +ΔE (n-1)i ),·……

[0051] The variable A is the azimuth angle, E is the elevation angle, and (n-1) is the number of auxiliary detection antennas.

[0052] This embodiment is generally used for satellite detection and control. For large-scale low-orbit satellite systems, tens of thousands of satellites need to be launched to form a satellite constellation. In order to improve the launch efficiency of ground rockets, it is often necessary to perform a multi-satellite mission with one rocket. At the moment of satellite-rocket separation, the low-orbit satellite group has not completely dispersed, and the ground measurement and control station antenna needs to quickly capture and track the low-orbit satellite group so that the satellite can adjust its attitude. However, the existing low-orbit satellite ground measurement and control systems mostly use large-aperture antennas in the millimeter-wave frequency band. For the large-aperture low-orbit satellite ground measurement and control systems in the millimeter-wave frequency band, due to the narrow beam width of the single ground antenna, at the moment of satellite-rocket separation, the beam formed in space by the ground station in a program-guided manner may not cover the actual low-orbit satellite group location area, and cannot quickly capture, track and adjust the attitude of the low-orbit satellite at the moment of satellite-rocket separation. However, in actual use, it is impossible to redeploy a large number of wide-beam antennas.

[0053] Therefore, in this embodiment, for the purpose of utilizing a large number of existing narrow beam antennas, this embodiment utilizes a large number of existing narrow beam antennas to form a cellular wide beam antenna for detection. Specifically, the measurement and control scheduling unit sends the ephemeris of the target satellite to the measurement and control ground-based servo feed system corresponding to each antenna, and the measurement and control ground-based servo feed system corresponding to the main detection antenna 1 generates a corresponding attitude control action to control the main detection antenna 1 according to the ephemeris, and the measurement and control ground-based servo feed system corresponding to the auxiliary detection antennas 2 to 6 generates its own auxiliary control action according to the attitude control action corresponding to the main detection antenna 1, and generates its own auxiliary control action according to the relative position of its own corresponding auxiliary beam detection space S2 to S6 and the main beam detection space S1 to control the auxiliary detection antenna.

[0054] With a single antenna, i.e., the main lobe narrow beam area of ​​the main detection antenna 1 pointing to the low-orbit satellite as the center circle, multiple other ground antennas, i.e., the narrow beams of multiple auxiliary detection antennas 2 to 6 are superimposed and expanded in a circle outside the center circle to form a honeycomb wide beam. The main detection antenna 1 is program-guided according to the satellite's ephemeris. While its azimuth and pitch are constantly changing over time, other auxiliary detection antennas 2 to 6 are also program-guided by loading different values ​​in their azimuth and pitch at all times, so that the beams of different antennas move parallel to the central beam, and different narrow beams are relatively stationary, so that the entire wide beam area pointed by all antennas moves synchronously according to the ephemeris. In other words, at the moment after the satellite-rocket separation, all antennas point to the satellite's beam area to form a honeycomb wide beam to capture and track the low-orbit satellite group. Once a narrow beam in the cellular wide beam completes the capture and tracking of a low-orbit satellite, the actual ephemeris information of the low-orbit satellite is immediately shared with other antenna units through the ground measurement and control scheduling unit. The ground measurement and control scheduling unit controls all main detection antennas and auxiliary detection antennas to uniformly point to the actual satellite target position detected by adjusting their respective azimuth and pitch attitudes. The cellular wide beam composed of the main beam detection space S1 and the auxiliary beam detection space S2~S6 is gathered and shrunk into a single beam, aimed at the actual satellite group target position, and all measurement and control antennas complete the capture, tracking and attitude adjustment of the low-orbit satellite group.

[0055] Further preferably, the number of antennas in the antenna group is 6.

[0056] like Figure 2 , 3 As shown, in this embodiment, since more ground antennas are required to generate a honeycomb wide beam, and the beams of different antennas have overlapping areas when multiple narrow beams are superimposed, it is necessary to reasonably plan the number of ground antennas to reduce the capture cost. At the moment of satellite-rocket separation, the coverage area where the main lobe beam width points to the satellite is a circle. The single antenna originally pointing to the satellite is the main detection antenna 1, and its main beam pointing to the satellite is used as the center circle. The antennas are superimposed on the periphery of the center circle to form a total of multiple ground measurement and control antennas. That is, the other auxiliary antennas point to the periphery of the center circle through beams. Since their beam widths are the same as those of the main detection antenna 1, the radius of the circle to which their beams point is also the same. The circumference of the center circle is evenly divided into equal parts, and the beams are extended and superimposed to the periphery to form a wide beam. When multiple antenna beams are extended and superimposed, in order to maximize the prevention of omissions in the beam coverage area, the beam pointing of different antennas inevitably has overlapping areas. The concept of ground measurement and control multi-antenna capture efficiency η is introduced, that is, the effective capture area S covered by the superposition of n ground measurement and control antenna beams at the position of the low-orbit satellite group. n , divided by the total capture area S when n antennas work independently, as follows:

[0057]

[0058] Next, the formula is derived and simplified, where the total capture area S when n antennas work independently is:

[0059] S=nπr 2 (2)

[0060] Where r is the radius of the circle covered by the satellite with the main lobe narrow beam of a single antenna.

[0061] Since the beams pointed by multiple ground measurement and control antennas have overlapping areas, the area of ​​the overlapping area is S'. The area S' of the overlapping area is calculated and simplified as:

[0062]

[0063] Then the effective capture area S covered by the n ground measurement and control antenna beam superposition method at the low-orbit satellite cluster position is n for:

[0064]

[0065] Finally, by substituting equations (3) and (4) into equation (1), we can obtain the ground measurement and control multi-antenna capture efficiency η:

[0066]

[0067] Then the derived formula is simulated by software. Taking into account most of the actual usage situations, when 4≤n≤10, the table and curve of the relationship between the antenna capture efficiency η and the total number of ground measurement and control antennas n are obtained, as shown in the table below. Based on this, we can choose the optimal number n of the total ground antennas under this ground antenna beam superposition method.

[0068] Table 1 Relationship between antenna capture efficiency η and total number of ground measurement and control antennas n

[0069]

[0070] From Table 1 and Figure 4 When the total number of ground antennas n = 6, the capture efficiency reaches a maximum of 90.82%. The final proposed ground measurement and control multi-antenna wide-beam system captures and tracks low-orbit satellites at the moment of satellite-rocket separation. Figure 1 shown.

[0071] from Figure 1 It can be seen that the narrow beams of the six ground antennas are superimposed and expanded to form a wide beam, which makes the beam coverage area of ​​the ground antenna pointing to the satellite larger. At the moment of separation of the satellite and the rocket, the main detection antenna 1 of the ground station is guided according to the program according to the satellite's ephemeris, and its azimuth and elevation data are (A t1 ,E t1 ),(At2 ,E t2 ),·······,(A ti ,E ti ),·······, at the same time, the other five auxiliary detection antennas produce different Δ values ​​on the azimuth and elevation of the main detection antenna 1. Their azimuth and elevation data are (A t1 +ΔA 11 ,E t1 +ΔE 11 ),(A t2 +ΔA 12 ,E t2 +ΔE 12 ),·······,(A ti +ΔA 1i ,E ti +ΔE 1i ),·······,(A t1 +ΔA 21 ,E t1 +ΔE 21 ),(A t2 +ΔA 22 ,E t2 +ΔE 22 ),·······,(A ti +ΔA 2i ,E ti +ΔE 2i ),·············, (A t1 +ΔA 51 ,E t1 +ΔE 51 ),(A t2 +ΔA 52 ,E t2 +ΔE 52 ),·······,(A ti +ΔA 5i ,E ti +ΔE 5i ),·······. Eventually, the beams of the six antennas pointing to the satellite area move synchronously as a whole. When one of the six antennas completes the capture and tracking of the low-orbit satellite, it can distribute the satellite ephemeris information to other measurement and control antennas through the ground measurement and control system. The other antennas uniformly point to the actual satellite target position detected. The cellular wide beam composed of the main beam detection space S1 and the auxiliary beam detection space S2~S6 converges and shrinks into a single beam, so that all measurement and control antennas can quickly complete the capture, tracking and attitude adjustment of the low-orbit satellite group.

[0072] Embodiment 2:

[0073] like Figure 5As shown, this embodiment provides a multi-narrow beam antenna detection control strategy for adjusting the attitudes of multiple narrow beam antennas to track the satellite when the target low-orbit satellite is separated from the rocket, including:

[0074] Step 1: The ground measurement and control scheduling unit sends the ephemeris to multiple measurement and control ground servo feed systems;

[0075] Step 2: The multiple measurement and control ground-based servo feed systems adjust the azimuth and elevation attitudes of the narrow beam antennas according to the ephemeris table to form a honeycomb beam detection space at the target detection point;

[0076] Step 3: When any one of the multiple measurement and control ground-based servo-feedback systems detects a target low-orbit satellite, the actual position of the target low-orbit satellite is sent to the ground measurement and control scheduling unit;

[0077] Step 4: The ground measurement and control scheduling unit updates the ephemeris table according to the actual position and returns to S1.

[0078] Therefore, in this embodiment, a multi-narrow beam antenna detection control strategy is proposed, and a ground measurement and control scheduling unit is used to send an expected ephemeris table to multiple measurement and control ground antenna feed systems. The multiple measurement and control ground antenna feed systems adjust the azimuth and pitch attitudes of the narrow beam antennas according to the ephemeris table. The narrow beams of the multiple antennas form an edge superposition and expansion of the beam space around the single antenna beam to form a honeycomb wide beam. The entire wide beam moves synchronously according to the ephemeris table, that is, the beams of different antennas move in parallel with the central beam. When any one of the multiple measurement and control ground antenna feed systems detects a target low-orbit satellite, and sends the actual position of the detected target low-orbit satellite to the ground measurement and control scheduling unit, the ground measurement and control scheduling unit updates the ephemeris table to other measurement and control ground antenna feed systems according to the actual position, and other antennas expand and superimpose at the edge of the new main beam detection space by adjusting the azimuth and pitch attitudes, so that the central main beam of the honeycomb wide beam detection space is always aligned with the actual low-orbit satellite target.

[0079] Through a multi-narrow beam antenna detection control strategy, the narrow beams of multiple antennas are superimposed to form a cellular wide beam, and according to the real satellite ephemeris, the center of the cellular wide beam is always aligned with the satellite target, and the entire cellular wide beam moves synchronously with the satellite.

[0080] Although the preferred embodiments of the present invention have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0081] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A multi-narrow beam antenna detection control system for tracking and capturing target detection objects, characterized in that: include: Antenna group; The antenna group specifically includes a main detection antenna and a plurality of auxiliary detection antennas; The main detection antenna forms a main beam detection space at the target detection point; The plurality of auxiliary detection antennas form a plurality of auxiliary beam detection spaces around the main beam detection space; The auxiliary beam detection space moves following the movement of the main beam detection space to form a honeycomb beam detection space at the target detection point; The target detection point is confirmed according to the target expected position of the target detection object; When any one antenna in the antenna group detects a target detection object, the target expected position is corrected according to the actual position of the target detection object; The antenna group adjusts the azimuth and pitch attitude according to the corrected expected target position.

2. A multi-narrow beam antenna detection and control system according to claim 1, characterized in that: It also includes a measurement and control scheduling unit and a measurement and control ground antenna servo feed system, wherein the measurement and control scheduling unit is a ground measurement and control scheduling unit; each of the measurement and control ground antenna servo feed systems corresponds to an antenna in the antenna group; The measurement and control scheduling unit generates the expected target position to the measurement and control ground-based antenna feed system, and the measurement and control ground-based antenna feed system controls the antenna to capture, track and adjust the attitude of the target detection object according to the expected target position.

3. A multi-narrow beam antenna detection and control system according to claim 2, characterized in that: The azimuth and elevation angles of the main detection antenna satisfy: (TO t1 ,AND t1 ),(TO t2 ,AND t2 ),·······,(TO ti ,AND ti ),·······; The azimuth angles and elevation angles of the multiple auxiliary detection antennas satisfy: (A t1 +ΔA 11 ,E t1 +ΔE 11 ),(A t2 +ΔA 12 ,E t2 +ΔE 12 ),·······,(A ti +ΔA 1i ,E ti +ΔE 1i ),·······,(A t1 +ΔA 21 ,E t1 +ΔE 21 ),(A t2 +ΔA 22 ,E t2 +ΔE 22 ),·······,(A ti +ΔA 2i ,E ti +ΔE 2i ),········,········,(A t1 +ΔA (n-1)1 ,E t1 +ΔE (n-1)1 ),(A t2 +ΔA (n-1)2 ,E t2 +ΔE (n-1)2 ),·……,(A ti +ΔA (n-1)i ,E ti +ΔE (n-1)i ),·…… Among which variable A is the number of probe antennas.

4. A multi-narrow beam antenna detection and control system according to claim 3, characterized in that: The difference between the azimuth angle and the elevation angle between the main detection antenna and the auxiliary detection antenna satisfies the requirement that the auxiliary beam detection space is superimposed along the periphery of the main beam detection space.

5. The multi-narrow beam antenna detection and control system according to claim 3, characterized in that: The relative position between each beam detection space in the honeycomb beam detection space is dynamically fixed.

6. The multi-narrow beam antenna detection and control system according to claim 1, characterized in that: The target detection object is a target satellite; The target detection point is determined according to the ephemeris of the target satellite.

7. The multi-narrow beam antenna detection and control system according to claim 1, characterized in that: The main beam detection space is circular; the auxiliary beam detection space is circular; the antennas in the antenna group have the same beam width; and the antennas in the antenna group are narrow beam antennas.

8. A multi-narrow beam antenna detection and control system according to claim 7, characterized in that: There is an overlapping portion between the auxiliary beam detection space and the main beam detection space, and the overlapping portion divides the circular contour of the main beam detection space equally.

9. A multi-narrow beam antenna detection and control system according to claim 8, characterized in that: The number of antennas in the antenna group is 6.

10. A multi-narrow beam antenna detection control strategy for adjusting the attitude of multiple narrow beam antennas to track the satellite when the target low-orbit satellite is separated from the rocket, characterized in that: include: The ground measurement and control dispatching unit sends the ephemeris to multiple measurement and control ground servo feed systems; The multiple measurement and control ground-based servo-feedback systems adjust the azimuth and elevation attitudes of the narrow beam antennas according to the ephemeris table to form a honeycomb beam detection space at the target detection point; When any one of the plurality of measurement and control ground-based servo-feedback systems detects a target low-orbit satellite, the actual position of the target low-orbit satellite is sent to the ground measurement and control scheduling unit; The ground measurement and control scheduling unit updates the ephemeris table according to the actual position.

Images