Method for rapidly completing satellite load detection surface target

Abstract

The invention discloses a method for rapidly completing a satellite load detection surface target. The method comprises the following steps: S1, obtaining N visible arc segments of a task satellite load detection surface target; s2, sorting the N visible arc segments according to a time sequence; s3, according to the sorting sequence, the optimal side swing angle theta i of the satellite load in the ith visible arc section is calculated, and i is larger than or equal to 1 and smaller than or equal to N; and S4, carrying out surface target detection on the satellite load in the ith visible arc section by taking the optimal side swing angle as theta i until the coverage rate BCR reaches 100%. According to the method, the optimal detection area can be obtained when the task satellite passes through the surface target by adjusting the load of the task satellite in the visible arc section to the optimal side swing angle theta i, so that the detection completion speed of the surface target is greatly increased, the detection completion time of the surface target can be shortened to about one half of that of a common method, and the detection efficiency is improved. Satellite resources are saved, and the utilization efficiency of the satellite resources is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite payload detection mission planning, and in particular to a method for quickly completing satellite payload detection of surface targets. Background Art

[0002] With the development of society, the demand for satellite payloads to detect targets on the surface is increasing. In order to make good use of limited satellite detection resources, it is necessary to do a good job in satellite payload mission planning and improve the efficiency of satellite payload use. When existing satellite payloads perform detection missions, the planning of the side swing angle is insufficient, resulting in the satellite payload not being able to achieve the best detection efficiency when performing detection, which affects the efficiency of satellite payload use and increases the time to complete the mission.

[0003] Patent document CN110203422B discloses a rapid response satellite orbit design method for surface target area detection. Although the application involves detection of surface target areas, it is mainly based on the satellite orbit design method and does not involve the adjustment of the satellite payload side swing angle. Summary of the invention

[0004] The purpose of the present invention is to provide a method for quickly completing the detection of surface targets by a satellite payload, so as to solve the problem that the side swing angle of the satellite payload is not optimized, resulting in low efficiency of satellite payload detection and a long time to complete the detection task when the satellite payload detects the surface target.

[0005] The purpose of the present invention can be achieved by the following technical scheme: A method for quickly completing satellite payload detection of surface targets, comprising the following steps:

[0006] S1. Obtain N visible arcs of the detection surface target of the mission satellite payload;

[0007] S2, sorting the N visible arcs in chronological order;

[0008] S3. Calculate the optimal side swing angle θ of the satellite payload detection surface target in the i-th visible arc segment according to the sorting order of the visible arc segments. i , where 1≤i≤N;

[0009] S4. According to the sorting order of the visible arc segments, the satellite payload in each visible arc segment detects surface targets at the optimal side swing angle θi until the coverage rate BCR reaches 100%.

[0010] Further: the acquisition of the visible arc segments in S1 includes the following steps:

[0011] S11, obtaining the boundary line coordinates of the surface target;

[0012] S12, obtaining six numbers of the mission satellite, and predicting the orbit of the mission satellite according to the six numbers;

[0013] S13. Determine the visible arc segment of the mission satellite according to the mission satellite orbit and the boundary line coordinates of the surface target.

[0014] Further: the basis for sorting the visible arc segments in time order in S2 is the start time of the visible arc segments.

[0015] Further: the optimal side swing angle θ of the satellite payload detecting the surface target in the i-th visible arc segment is calculated in S3 i The following steps are involved:

[0016] S31, calculating the detection area S(θ) of the satellite payload detection surface target in the i-th visible arc segment;

[0017] S32, calculate the maximum increment f(θ) of the target coverage area F(i) of the i-th visible arc segment according to the change of the detection area S(θ) of the i-th visible arc segment i ), the formula is:

[0018]

[0019] Where F(i-1) is the target coverage area of ​​the i-1th visible arc segment;

[0020] S33, based on the maximum value f(θ i ) Determine the optimal roll angle θ of the satellite payload in the i-th visible arc segment i .

[0021] Further: the formula for obtaining the coverage area F(i) in S32 is:

[0022] F(i)=f(1)+f(2)…f(i).

[0023] Further: the maximum increment f(θ i ), the step range of the satellite payload side swing angle θ in the i-th visible arc segment is 0.1°~1°.

[0024] Further: the formula for obtaining the coverage rate BCR in S4 is:

[0025] BCR=F(i) / S*%

[0026] Where S is the total detection area of ​​the surface target.

[0027] Beneficial effects of the present invention:

[0028] 1. The present invention adjusts the mission satellite payload within the visible arc segment to an optimal side swing angle of θ i, so that the mission satellite can obtain the best detection area when passing the surface target, thereby greatly increasing the detection completion speed of the surface target. The detection completion time of the surface target can be shortened to about one half of that of the ordinary method, saving satellite resources and improving the utilization efficiency of satellite resources.

[0029] 2. The present invention divides the visible arc segments and obtains the maximum increment f(θ i ), determine the optimal side swing angle θ i , the mission satellite's side swing angle can be adjusted to the optimal angle, so that the detection coverage efficiency of the mission satellite in each visible arc segment is the highest, thereby improving the detection completion speed of surface targets. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic flow chart of a method for quickly completing satellite payload detection of surface targets according to the present invention;

[0031] Figure 2 Schematic diagram of the change of the side swing angle θ and the detection area S(θ) of the present invention;

[0032] Figure 3 This is a schematic diagram of dividing visible arc segments of multiple satellite payloads of the present invention;

[0033] Figure 4 This is a schematic diagram of cumulative calculation of single coverage and total coverage of visible arc segments of the present invention;

[0034] Figure 5 A schematic diagram of forming a detection area for a single satellite payload detection surface target according to the present invention;

[0035] Figure 6 It is a schematic diagram of forming a detection area by detecting surface targets with multiple satellite payloads according to the present invention. DETAILED DESCRIPTION

[0036] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar symbols throughout represent the same or similar elements or elements with the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0037] like Figure 1-6 As shown, the present invention discloses a method for quickly completing satellite payload detection of surface targets, comprising the following steps:

[0038] S1. Obtain N visible arcs of the detection surface target of the mission satellite payload;

[0039] S2, sorting the N visible arcs in chronological order;

[0040] S3. Calculate the optimal side swing angle θ of the satellite payload detection surface target in the i-th visible arc segment according to the sorting order of the visible arc segments. i , where 1≤i≤N;

[0041] S4, according to the order of visible arc segments, the satellite payload in each visible arc segment is set at the optimal side swing angle θ i Perform surface target detection until the coverage rate BCR reaches 100%.

[0042] like Figure 5 , 6 As shown, first determine the surface target area of ​​the task, for example, the surface target area can be an industrial area, a forest, or a province, and then determine the task start time, for example, the task start time is July 12, 2019.

[0043] The detection area of ​​a visible arc segment of a single low-orbit detection satellite is limited. In order to quickly complete the detection task of surface targets, it is generally necessary to rationally utilize multiple transit detection satellites to improve detection efficiency and shorten the completion time. Figure 3 , 4 As shown, when multiple detection satellites are used, it is necessary to calculate the visible arc segment of each satellite when it passes over the surface target.

[0044] The visible arc segments can be obtained based on the determined surface target area and mission start time, which mainly includes the following steps:

[0045] S11, obtaining the boundary line coordinates of the surface target;

[0046] S12, obtaining six numbers of the mission satellite, and predicting the orbit of the mission satellite according to the six numbers;

[0047] S13. Determine the visible arc segment of the mission satellite according to the mission satellite orbit and the boundary line coordinates of the surface target.

[0048] The boundary line coordinates of the surface target can be obtained through query, and the six elements of the mission satellite can also be obtained through query. The orbit of the mission satellite is predicted based on the six elements. Based on the orbit of the mission satellite and the boundary line coordinates of the surface target, the visible arc segment of the mission satellite passing the surface target can be calculated, such as Figure 4 As shown, the visible arc segment includes the arc segment start time and the arc segment end time, and the obtained N visible arc segments are sorted, such as Figure 4 As shown, the visible arcs can be sorted in chronological order according to their start time.

[0049] In a visible arc segment, the sensor sub-satellite point data can be obtained according to the mission satellite orbit parameters, payload parameters and side swing angle θ, and the intersection of the surface target and the sensor sub-satellite point area is calculated according to the step size to calculate the detection area S(θ) of the mission satellite, as follows: Figure 2As shown in the figure, the mission satellite's roll angle θ can be adjusted between (-M~M), and this adjustment can be achieved by controlling the satellite through the ground station. When the roll angle θ is between (-M~M), the detection area S(θ) changes due to the roll angle θ, presenting a sine wave-like graph. There is an optimal roll angle θ i , when the mission satellite side swing angle is θ i It can achieve the fastest growth rate of mission satellite detection coverage area.

[0050] Specifically, the optimal roll angle θ for the satellite payload to detect the surface target in the i-th visible arc segment is i The following steps are involved:

[0051] S31, calculating the detection area S(θ) of the satellite payload detection surface target in the i-th visible arc segment;

[0052] S32, calculate the maximum increment f(θ) of the target coverage area F(i) of the i-th visible arc segment according to the change of the detection area S(θ) of the i-th visible arc segment i ), the formula is:

[0053]

[0054] Where F(i-1) is the target coverage area of ​​the i-1th visible arc segment;

[0055] S33, based on the maximum increment f(θ i ) Determine the optimal roll angle θ of the satellite payload in the i-th visible arc segment i .

[0056] like Figure 5 , 6 As shown, for example: the UOSAT 2(U0-11)-14781 satellite is a detection satellite in the first visible arc segment, and its detection area is S(θ). When θ=θ1, S(θ1)=f(θ1)=F(1). The LUSAT 0-191-20442 satellite is a detection satellite in the second visible arc segment, and its detection area is S(θ). When θ=θ2, F(2)=S(θ2)+S(θ1)-S(θ2)∩S(θ1), and f(θ2)=S(θ2)-S(θ2)∩S(θ1).

[0057] The formula for obtaining the coverage area F(i) is:

[0058] F(i)=f(θ1)+f(θ1)……f(θ i ).

[0059] Maximum increment f(θ i ) is obtained as follows:

[0060] f(θi )=S(θ i )-S(θ i )∩S(θ i-1 )……S(θ1).

[0061] Calculate the maximum increment f(θ i ), the angle of θ can be changed by equal steps, and the step value can be changed by 0.01°, 2°, etc. However, if the step value is too large, it will affect the maximum increment f(θ i ) is too small to affect the maximum increment f(θ i ) calculation speed, the preferred step range of θ angle is 0.1°~1°, which can more accurately obtain the maximum increment f(θ i ).

[0062] By continuously superimposing multiple maximum increments of visible arc segments f(θ°), the satellite payload detection coverage rate BCR can be quickly improved. The calculation formula of the coverage rate BCR is:

[0063] BCR=F(i) / S*%

[0064] Where S is the total detection area of ​​the surface target, until the detection coverage rate BCR reaches 100%.

[0065] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

[0066] It should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0067] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0068] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0069] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

Claims

1. A method for quickly completing satellite payload detection of surface targets, characterized in that: The following steps are involved: S1. Obtain N visible arcs of the detection surface target of the mission satellite payload; S2, sorting the N visible arcs in time order; S3. Calculate the optimal side swing angle θ of the satellite payload detection surface target in the i-th visible arc segment according to the sorting order of the visible arc segments. i , where 1≤i≤N; S4, according to the order of visible arc segments, the satellite payload in each visible arc segment is set at the optimal side swing angle θ i Perform surface target detection until the coverage rate BCR reaches 100%.

2. A method for quickly completing satellite payload detection of surface targets according to claim 1, characterized in that: The acquisition of the visible arc segments in S1 includes the following steps: S11, obtaining the boundary line coordinates of the surface target; S12, obtaining six numbers of the mission satellite, and predicting the orbit of the mission satellite according to the six numbers; S13. Determine the visible arc segment of the mission satellite according to the mission satellite orbit and the boundary line coordinates of the surface target.

3. A method for quickly completing satellite payload detection of surface targets according to claim 1, characterized in that: The basis for sorting the visible arc segments in time order in S2 is the start time of the visible arc segments.

4. A method for quickly completing satellite payload detection of surface targets according to claim 1, characterized in that: In S3, the optimal roll angle θ for detecting the surface target by the satellite payload in the i-th visible arc is calculated. i The following steps are involved: S31, calculating the detection area S(θ) of the satellite payload detection surface target in the i-th visible arc segment; S32, calculate the maximum increment f(θ) of the target coverage area F(i) of the i-th visible arc segment according to the change of the detection area S(θ) of the i-th visible arc segment i ), the formula is: Where F(i-1) is the target coverage area of ​​the i-1th visible arc segment; S33, based on the maximum increment f(θ i ) Determine the optimal roll angle θ of the satellite payload in the i-th visible arc segment i .

5. The method for quickly completing satellite payload detection of surface targets according to claim 1, characterized in that: The formula for obtaining the coverage area F(i) in S32 is: F(i)=f(1)+f(2)...··f(i).

6. The method for quickly completing satellite payload detection of surface targets according to claim 1, characterized in that: The maximum increment f(θ i ), the step range of the satellite payload side swing angle θ in the i-th visible arc segment is 0.1°~1°.

7. The method for quickly completing satellite payload detection of surface targets according to claim 1, characterized in that: The formula for obtaining the coverage rate BCR in S4 is: BCR=F(i) / S*% Where S is the total detection area of ​​the surface target.

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