Optimal motion range selection method for coiled antenna of aerospace ground equipment based on single feature point

Abstract

The present invention discloses a method for optimizing the movement interval of a coiled antenna of aerospace ground equipment based on a single feature point, which specifically includes the following steps: Step 1, extracting the geodetic angle of the antenna movement interval feature point according to the target orbit forecast; Step 2, judging whether the antenna azimuth movement passes through zero according to the antenna movement interval feature point information and the antenna's inherent heading angle; Step 3, calculating the azimuth intermediate winding angle according to the geodetic angle of the movement interval feature point and the antenna's inherent heading angle; Step 4, optimizing the antenna azimuth movement interval. Compared with traditional judgment methods, the method for optimizing the movement interval of a coiled antenna of aerospace ground equipment based on a single feature point of the present invention reduces the number of associated judgment feature points, simplifies the judgment process, greatly reduces the computational workload, improves the efficiency of task execution, and has the advantages of a simple calculation process, a wide range of applications, and good engineering applicability, and has good practicality.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace measurement and control, and in particular relates to a method for optimizing the motion interval of a coiled antenna of aerospace ground equipment based on a single characteristic point. Background Art

[0002] Antennas for aerospace ground station equipment are generally divided into fully movable antennas and limited-motion antennas. The azimuth axis of a fully movable antenna generally adopts a slip ring form. By connecting cables such as high-frequency and medium-frequency slip rings and power amplifier slip rings, the antenna can move unrestricted around the azimuth axis N×360°. In many fixed and vehicle-mounted systems, limited-motion antennas are used to reduce system complexity and improve system reliability. Their azimuth axis generally adopts a winding form. When the winding form is adopted, the azimuth movement of the antenna will be limited by the range of motion (for example, -355° to +355°). It is necessary to avoid the limit and consider optimizing the azimuth movement range so that the connecting cable is not wound too tightly.

[0003] To ensure the normal execution of the mission, the antenna control unit needs to map the forecast data of the winding antenna azimuth range of 0° to +360° to the range of -355° to 0° (negative circle) or 0° to +355° (positive circle) to avoid the limitation of the movement range. The antenna control unit's strategy for autonomously judging and processing azimuth movement is: if the antenna azimuth movement passes through zero or exceeds the limit, its movement range is uniquely determined and there is no optimization problem. If the antenna movement does not pass through zero or exceed the limit, there are two situations in its movement range: positive circle and negative circle. The antenna control unit selects one of the movement ranges based on the principle of proximity and drives the antenna to guide from the current position to the target entry waiting point.

[0004] Currently, the antenna control unit does not judge the quality of the antenna's movement range. If the antenna control unit autonomously selects a poor movement range, it may cause the antenna movement winding angle to be too large and too close to the limit position, increasing the risk of impacting the limit position. In addition, the cable is wound tightly, which may cause physical damage or even breakage due to tension. The traditional method for determining the azimuth optimized movement range is to calculate the azimuth winding angle of the entry and exit feature points and their mapping angles in the negative circle, compare them, and select the movement range with the smaller maximum winding angle as the optimized movement range. This method selects a large number of feature points, the process is relatively complex, and the computational workload is large. Summary of the Invention

[0005] The purpose of the present invention is to provide a method for optimizing the motion interval of a coiled antenna of aerospace ground equipment based on a single feature point, which solves the problems of a large number of feature points to be selected, a relatively complex process and a large computational workload in the existing methods.

[0006] The technical solution adopted in the present invention is:

[0007] The method for optimizing the motion interval of a coiled antenna of aerospace ground equipment based on a single characteristic point specifically comprises the following steps:

[0008] Step 1: Extract the geodetic angle of the characteristic points in the antenna motion interval according to the target orbit prediction;

[0009] Step 2: Determine whether the antenna azimuth motion crosses zero based on the characteristic point information of the antenna motion interval and the inherent heading angle of the antenna;

[0010] Step 3: Calculate the azimuth intermediate winding angle based on the geodetic angle of the feature point in the motion interval and the inherent heading angle of the antenna;

[0011] Step 4: Optimize the antenna azimuth movement interval.

[0012] The present invention is also characterized in that:

[0013] Step 1 is as follows:

[0014] For low-Earth orbit targets, the target's inbound and outbound geodetic angles are extracted based on the target orbit forecast. The inbound and outbound geodetic angles are directly calculated based on the orbit forecast in the geodetic coordinate system.

[0015] For deep space orbit targets, their ballistic trajectories are asymmetric. Based on the target orbit forecast, the target's approach azimuth geodetic angle, departure azimuth geodetic angle, and middle angle of the azimuth motion interval are extracted. The middle angle of the azimuth motion interval is calculated as the arithmetic mean of the approach azimuth geodetic angle and the departure azimuth geodetic angle.

[0016] In step 2, it is determined whether the antenna azimuth motion crosses zero, which specifically includes the following steps:

[0017] Step 2.1: Based on the feature point information of the inbound azimuth geodetic angle and the outbound azimuth geodetic angle, determine whether the antenna motion interval contains the angle value of the antenna's inherent heading angle Ψ0. If the motion interval contains the angle value of the heading angle, the antenna motion crosses zero.

[0018] In step 2.2, if the azimuth motion interval does not include the heading angle value, the antenna motion does not exceed zero.

[0019] In step 3, the antenna azimuth intermediate winding angle is calculated, which includes the following sub-steps:

[0020] Step 3.1: For low-Earth orbit targets, the antenna trajectory is generally a symmetrical curve. The winding angle is calculated based on the over-the-top azimuth angle by subtracting the heading angle Ψ0 from the over-the-top azimuth angle.

[0021] Step 3.2: For deep space orbit targets, the antenna motion trajectory is generally an asymmetric arc segment. The arithmetic mean of the inbound azimuth and the outbound azimuth is calculated to obtain the intermediate azimuth angle. The heading angle Ψ0 is subtracted from the intermediate azimuth angle to obtain the intermediate azimuth winding angle.

[0022] Step 4 specifically includes the following steps:

[0023] Step 4.1, based on the azimuth intermediate winding angle calculated in step 3, comparing the quantitative relationship between the azimuth intermediate winding angle and the symmetry axis 180°;

[0024] Step 4.2, based on the comparison result in step 4.1, perform the optimal judgment on the antenna azimuth movement interval: if the azimuth middle winding angle is less than or equal to 180°, the antenna azimuth movement interval is preferably a positive circle; if the azimuth middle winding angle is greater than 180°, the antenna azimuth movement interval is preferably a negative circle.

[0025] In step 4, the mirror principle is used to determine the optimal motion interval, specifically:

[0026] Azimuth intermediate mapping angle A" m is the azimuthal middle winding angle A′ m The relationship between the mapping angle in the negative circle motion range is as follows:

[0027] A" m =A′ m -360° (1)

[0028] A" m +180°=A′ m -180° (2)

[0029] When A′ m =180°, A" m =-180°, A′ m and A" m Symmetrical about 0° on the winding angle coordinate axis, the winding degrees of the positive and negative circles are the same;

[0030] When A′ m When <180°, the azimuth motion interval is closer to the coordinate origin than its mapping interval in the negative circle, so the winding degree is smaller, and the positive circle is selected as the optimal motion interval;

[0031] When A′ m When the angle is >180°, the azimuth motion interval is farther away from the coordinate origin than its mapping interval in the negative circle, so the winding degree is greater, and the negative circle is selected as the optimized motion interval.

[0032] The present invention provides a method for optimizing the movement range of coiled antennas for aerospace ground equipment based on a single feature point. This method utilizes the mirror principle to address the limited range of movement of coiled antennas for aerospace ground station equipment, as well as the requirements for rapid arrival at waiting points and safe antenna operation. This method utilizes the principle of mirrors and proposes a method for determining the optimal movement range of coiled antennas based on target orbit prediction and installation heading angle. This method can quickly and accurately determine the optimal movement range for coiled antennas. Compared to traditional methods for comprehensive judgment of entry and exit feature points, the method reduces the number of selected associated judgment feature points from two to one, and streamlines the main calculation steps from four to one. This streamlines the judgment process and significantly reduces the computational workload. It can quickly and accurately determine the optimal movement range for coiled antennas, particularly for low-Earth orbit target antennas, improving mission efficiency. The method provided by the present invention is suitable for quickly determining the optimal movement range for coiled antennas in ground-based fixed / vehicle-mounted measurement and control, data transmission reception, radar detection, and other equipment. This invention can improve antenna control and display software, intuitively determine the optimal azimuth movement range, and drive the antenna to track and measure targets according to the optimized movement range. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a flow chart of a method for optimizing the movement interval of a coiled antenna of aerospace ground equipment based on a single characteristic point of the present invention;

[0034] Figure 2 This is a schematic diagram of the optimized motion interval of the low-orbit target azimuth in the motion interval optimization method of the coiled antenna of aerospace ground equipment based on a single feature point;

[0035] Figure 3 This is a schematic diagram of the zero crossing of the azimuth motion of a low-orbit target in the method for optimizing the motion interval of a coiled antenna of aerospace ground equipment based on a single feature point;

[0036] Figure 4 This is a schematic diagram of the optimized motion interval of the deep space target azimuth in the motion interval optimization method of the coiled antenna of aerospace ground equipment based on a single feature point. DETAILED DESCRIPTION

[0037] The following describes in detail the method for optimizing the movement interval of the coiled antenna of aerospace ground equipment based on a single characteristic point of the present invention in conjunction with the accompanying drawings and specific embodiments.

[0038] In the steps of the method for optimizing the movement interval of the coiled antenna of aerospace ground equipment based on a single characteristic point of the present invention, the definitions related to the movement of the coiled antenna are shown in Table 1 below.

[0039] Table 1 Definitions related to coiled antenna motion

[0040]

[0041]

[0042]

[0043] The scenario in this embodiment is as follows: the space ground station equipment takes a certain S / X unified measurement and control system (with a fixed heading angle of 31.17°) as an example; the mission targets include two types: target 1 is a low-Earth orbit target with an orbital altitude of approximately 380 kilometers, and target 2 is a deep space orbit target; the antenna motion range includes positive circle motion, negative circle motion, and azimuth zero crossing.

[0044] Example 1.

[0045] Mission scenario: Mission objective 1 (low Earth orbit), antenna optimization range is negative loop motion. Azimuth mid-wind angle 180° method is used for determination.

[0046] Step S1: Extract the characteristic point information of the antenna motion interval according to the target orbit prediction result, as shown in Table 2.

[0047] Table 2 Antenna tracking target motion feature points

[0048]

[0049] Step S2: Based on the target orbit prediction feature point information, it is determined that the antenna's inherent heading angle of 31.17° is not within the azimuth motion range and the antenna motion does not exceed zero.

[0050] In step S3, the over-the-top azimuth winding angle is calculated as 187.431° based on the over-the-top azimuth angle of the target feature point of 218.601° and the antenna heading angle of 31.17°. Here, the over-the-top azimuth winding angle is a special case of the azimuth intermediate winding angle.

[0051] In step S4, the over-the-top azimuth winding angle (the mid-azimuth winding angle) of 187.431° is compared with the symmetry axis of 180°. If the angle is greater than 180°, the antenna azimuth optimization motion interval can be quickly determined to be a negative loop. The relevant calculation results are shown in Table 3.

[0052] Table 3 Calculation results of low-orbit target azimuth motion interval

[0053]

[0054] Example 2.

[0055] Mission scenario: Mission objective 1 (low Earth orbit), antenna azimuth motion crosses zero.

[0056] The antenna motion characteristic points are shown in Table 4. It can be directly seen that the antenna motion spans the positive and negative circles and is limited by the azimuth motion range of the coiled antenna. There is a unique motion interval and no optimization is required.

[0057] Table 4 Calculation results of antenna azimuth zero-crossing motion winding angle

[0058]

[0059] Example 3.

[0060] Example 3 Mission scenario: Mission target 2 (deep space orbit), the antenna motion trajectory is an asymmetric arc segment, and the antenna optimization motion range is a positive circle motion. The azimuth intermediate winding angle 180° method is used for judgment.

[0061] The tracking arc's mid-azimuth angle (the arithmetic mean of the inbound and outbound azimuths) was selected as 68.96°, with a winding angle of 37.79°. Using the 180° mid-azimuth winding angle method, we can quickly determine that the azimuth optimization motion interval is a positive circle motion. The relevant calculation results are shown in Table 5.

[0062] Table 5 Calculation results of deep space target azimuth motion interval

[0063]

[0064] Comparative Example.

[0065] Comparative Example Mission Scenario: Mission Target 1 (Low Earth Orbit), Antenna Optimization Movement Range is Negative Loop Movement. The mission scenario and target orbit data are the same as those in Example 1, and the traditional method is used for judgment.

[0066] Step 1: According to the target orbit prediction results, extract the characteristic point information of the antenna motion interval in Table 2, including the geodetic angle of the inbound azimuth of 304.115° and the geodetic angle of the outbound azimuth of 129.836°.

[0067] Step 2: Based on the geodetic angles of the target feature points inbound and outbound directions and the antenna heading angle of 31.17°, the inbound and outbound azimuth winding angles are calculated to be 272.945° and 98.666°, respectively. The mapping angles of the winding angles to the negative circle are also calculated to be -87.055° and -261.334°, respectively.

[0068] Step 3: Take the absolute value of the entry / exit orientation mapping angles and compare them pairwise with the entry / exit winding angles. The maximum winding angle for the positive loop is 272.945°, with a maximum winding degree of 76.88%. The maximum winding angle for the negative loop is 261.334°, with a maximum winding degree of 73.62%. The smaller winding degree, 261.334°, is selected, and the negative loop motion range is designated as the optimized range. The relevant calculation results are shown in Table 6.

[0069] Table 6 Calculation results of azimuth motion of low-orbit target antenna

[0070]

[0071] By comparing Example 1 with the comparative example, it is shown that for the problem of determining the azimuth optimization movement interval of the coiled antenna, the method of using the azimuth intermediate coiling angle of 180° is consistent with the results of the traditional determination method, but the determination process is simpler and the computational workload is greatly reduced.

[0072] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiment. All technical solutions based on the concept of the present invention are within the scope of protection of the present invention. It should be noted that for those skilled in the art, various improvements and modifications that do not depart from the principles of the present invention should be considered as within the scope of protection of the present invention.

[0073] Compared with traditional judgment methods, the present invention's method for optimizing the motion interval of a coiled antenna of aerospace ground equipment based on a single feature point reduces the number of associated judgment feature points, simplifies the judgment process, greatly reduces the computational workload, and improves the efficiency of task execution. It also has the advantages of a simple calculation process, a wide range of applications, and good engineering applicability, and has good practicality.

Claims

1. A method for optimizing the motion interval of a coiled antenna of aerospace ground equipment based on a single feature point, characterized in that: The specific steps include: Step 1: Extract the geodetic angle of the characteristic points in the antenna motion interval according to the target orbit prediction; Step 2: Determine whether the antenna azimuth motion crosses zero based on the characteristic point information of the antenna motion interval and the inherent heading angle of the antenna; Step 3: Calculate the azimuth intermediate winding angle based on the geodetic angle of the feature point in the motion interval and the inherent heading angle of the antenna; Step 4, performing antenna azimuth movement interval optimization, step 4 specifically includes the following steps: Step 4.1, based on the azimuth intermediate winding angle calculated in step S3, comparing the quantitative relationship between the azimuth intermediate winding angle and the symmetry axis 180°; Step 4.2: Based on the comparison result in step 4.1, the antenna azimuth movement interval is optimized: if the azimuth middle winding angle is less than or equal to 180°, the antenna azimuth movement interval is determined to be a positive circle; if the azimuth middle winding angle is greater than 180°, the antenna azimuth movement interval is determined to be a negative circle; The mirror principle is used to determine the optimal motion range, specifically: Azimuth median mapping angle is the azimuthal middle winding angle The relationship between the mapping angle in the negative circle motion range is as follows: （1） （2） when hour, , and Symmetrical about 0° on the winding angle coordinate axis, the winding degrees of the positive and negative circles are the same; when When , the azimuth motion interval is closer to the coordinate origin than its mapping interval in the negative circle, so the winding degree is smaller, and the positive circle is selected as the optimal motion interval; when When , the azimuth motion interval is farther away from the coordinate origin than its mapping interval in the negative circle, so the winding degree is larger, and the negative circle is selected as the optimized motion interval.

2. The method for optimizing the movement interval of a coiled antenna of aerospace ground equipment based on a single feature point according to claim 1, characterized in that: Step 1 is as follows: For low-Earth orbit targets, the target's inbound and outbound geodetic angles are extracted based on the target orbit forecast. The inbound and outbound geodetic angles are directly calculated based on the orbit forecast in the geodetic coordinate system. For deep space orbit targets, their ballistic trajectories are asymmetric. Based on the target orbit forecast, the target's approach azimuth geodetic angle, departure azimuth geodetic angle, and middle angle of the azimuth motion interval are extracted. The middle angle of the azimuth motion interval is calculated as the arithmetic mean of the approach azimuth geodetic angle and the departure azimuth geodetic angle.

3. The method for optimizing the movement interval of a coiled antenna of aerospace ground equipment based on a single feature point according to claim 1, characterized in that: In step 2, it is determined whether the antenna azimuth motion crosses zero, which specifically includes the following steps: Step 2.1: Based on the feature point information of the inbound azimuth geodetic angle and the outbound azimuth geodetic angle, determine whether the antenna motion interval contains the angle value of the antenna's inherent heading angle Ψ0. If the motion interval contains the angle value of the heading angle, the antenna motion crosses zero. In step 2.2, if the azimuth motion interval does not include the angle value of the heading angle, the antenna motion does not exceed zero.

4. The method for optimizing the movement interval of a coiled antenna of aerospace ground equipment based on a single feature point according to claim 1, characterized in that: In step 3, the antenna azimuth intermediate winding angle is calculated, which includes the following sub-steps: Step 3.1: For low-Earth orbit targets, the antenna trajectory is a symmetrical curve. The winding angle is calculated based on the over-the-top azimuth angle by subtracting the heading angle Ψ0 from the over-the-top azimuth angle. Step 3.2: For deep space orbit targets, the antenna motion trajectory is generally an asymmetric arc segment. The arithmetic mean of the inbound azimuth and the outbound azimuth is calculated to obtain the intermediate azimuth angle. The heading angle Ψ0 is subtracted from the intermediate azimuth angle to obtain the intermediate azimuth winding angle.

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