General satellite payload energy constraint testing method and device

Abstract

The present invention provides a universal satellite payload energy constraint verification method and apparatus. The method comprises: dividing the satellite operating time into different satellite sub-periods; configuring satellite payload action condition results according to each of the divided satellite sub-periods; and performing constraint item verification within each satellite sub-period based on the configured payload action condition results within each satellite sub-period. The universal satellite payload energy constraint verification method and apparatus provided by the present invention can complete satellite payload energy constraint verification using simple judgment logic.

Description

Technical Field

[0001] The present invention relates to the technical field of remote sensing satellite planning, and in particular to a universal satellite payload energy constraint inspection method and device. Background Art

[0002] The purpose of remote sensing satellite payload constraint verification is to ensure that ground control systems can efficiently and safely utilize remote sensing satellites to carry out missions, maximizing the safety of remote sensing satellites and ground mission requirements. Satellite energy constraint verification primarily examines satellite operating hours and operating times. Operating hours are generally defined as satellite imaging or data transmission time, while operating times generally refer to satellite rollovers, payload power-on / off cycles, and data transmission power-on / off cycles. Traditional satellite energy constraint descriptions directly provide operating hours and operating times under different conditions. Newly developed satellites are developing energy balance calculation modules in the hope of addressing the challenges of satellite energy constraint verification and improving satellite on-orbit efficiency. Traditionally, satellite energy constraints are defined through documented descriptions. Because different satellite development organizations consider different charging and discharging principles and methods, the satellite energy constraints described vary. This results in complex energy constraint modeling for different satellites and makes it difficult to develop a reusable and standardized verification model. Currently, no relevant research results exist to support this work. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a universal satellite payload energy constraint inspection method and device, which can complete the satellite payload energy constraint inspection with simple judgment logic.

[0004] To solve the above technical problems, the present invention provides a universal satellite payload energy constraint verification method, which includes: dividing the satellite operating time into different satellite sub-periods; executing satellite payload action condition result configuration according to each divided satellite sub-period; and performing constraint item verification in each satellite sub-period based on the payload action condition result configuration in each satellite sub-period.

[0005] In some implementations, the method further includes: before dividing the satellite operating time into different satellite sub-periods, pre-processing the payload action queue.

[0006] In some embodiments, pre-processing of the load action queue includes: merging related load actions.

[0007] In some implementations, the satellite operating duration is divided into different satellite sub-periods, including: dividing the satellite operating duration into different satellite sub-periods according to a sliding division method, a designated time division method, or a comprehensive division method.

[0008] In some embodiments, the satellite operating time is divided into different satellite sub-periods according to the sliding division method, including the following steps: Step 1: Arrange the satellite payload actions in ascending order according to the action start time; Step 2: Obtain the payload action with the earliest start time in the queue, and set its start time as T 10 , the end time is T 11 ; Step 3: Get the sub-period of this sliding (perform constraint check within the sub-period), whose start time is T 1S =T 10 , the end time is T 1E =T 10 + L; Step 4: Find the first load action in the queue that is not included in the above sub-period, and set its start time as T 20 , the end time is T 21 ; Step 5: Let ΔT = T 20 -T 1E , if ΔT≥(T 11 -T 10 ), then jump to step 7; Step 6: Get a new sliding sub-period, whose start time is T 2S =T 10 +ΔT, end time is T 2E =T 2S +L; Step 7: Remove the first item from the queue. If the queue is not empty, return to step 2.

[0009] In some embodiments, the designated time division method includes: a bracketed number division method and a shadow area and sunlit area division method.

[0010] In some embodiments, the satellite operating time is divided into different satellite sub-periods according to the specified time division method, including: the first step: arranging the sub-period separation point moments in ascending time order; the second step: obtaining the first time T0 and the second time T1 in the queue; the third step: obtaining the sub-period, whose start time is T S =T0, end time is T E =T1; Step 4: Remove the first moment in the queue. If the number of queues is greater than or equal to 2, return to step 2, otherwise end.

[0011] In addition, the present invention also provides a universal satellite payload energy constraint verification device, which includes: one or more processors; a storage device for storing one or more programs, and when the one or more programs are executed by the one or more processors, the one or more processors implement the universal satellite payload energy constraint verification method described above.

[0012] After adopting such a design, the present invention has at least the following advantages:

[0013] The present invention completes the inspection of the energy constraints of the satellite payload through simple judgment logic. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The above is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0015] Figure 1 It is a flow chart of the general satellite payload energy constraint verification method;

[0016] Figure 2 It is a flow chart of satellite payload action queue preprocessing;

[0017] Figure 3 It is a schematic diagram of sliding division into sub-periods;

[0018] Figure 4 It is a schematic diagram of dividing a specified time into sub-periods. DETAILED DESCRIPTION

[0019] The preferred embodiments of the present invention are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0020] The technical problem to be solved by the present invention is to provide a universal satellite payload energy constraint verification method based on traditional constraint descriptions for energy constraints imposed by different remote sensing satellites on payload usage. The present invention has the characteristics of simple judgment logic and strong versatility.

[0021] The technical problem to be solved by the present invention is achieved by the following technical solutions:

[0022] A general satellite payload energy constraint verification method for traditional constraint description includes the following steps:

[0023] (1) Satellite payload action queue preprocessing;

[0024] (2) Satellite sub-period division;

[0025] (3) Satellite payload action condition result configuration;

[0026] (4) Initial value setting, iteration and judgment of constraint items within the sub-period.

[0027] (5) Return the test results.

[0028] This method mainly implements constraint checking through the following steps: satellite payload action queue preprocessing; satellite sub-period division; satellite payload action condition result configuration; constraint item initial value setting, iteration and judgment within the sub-period.

[0029] a) Satellite payload action queue preprocessing

[0030] The primary focus of satellite energy constraint verification is the operating time and number of payload actions per unit time. When calculating cumulative operating time and number of actions, the correlation between similar payload actions must be considered. For example, some remote sensing satellites can combine adjacent imaging actions. Therefore, when calculating operating time and number of actions in these situations, it is necessary to first combine related payload actions and then verify whether the constraints are met by different time intervals.

[0031] The purpose of satellite payload action queue preprocessing is to convert the input payload action through parameter conversion and generate a new payload action to replace the payload action in the original queue, so as to facilitate the use of its parameters for conditional result configuration item matching and constraint item iteration value calculation.

[0032] The satellite payload action queue preprocessing is implemented by using a rule-based payload action parameter conversion method. The preprocessing process is as follows: Figure 2 .

[0033] b) Satellite sub-time division

[0034] The requirements for satellite operating hours and frequency can be broken down into operating hours and frequency requirements within different sub-periods. For example, some satellites have a maximum payload operating time of T1 during the day and T2 at night. To verify these constraints, the entire satellite period can be broken down into a series of sub-periods in the sunlit or shaded areas, and constraint checks can be performed within each sub-period.

[0035] There are three methods for dividing satellite sub-periods: sliding division, designated time division (including circle number division and shadow and sun zone division), and comprehensive division. The sliding division method refers to sliding sequentially within the entire time interval according to the specified time length. Regardless of the position of the period, the payload actions included in the period must meet the working time and number of working times requirements. The designated time division method means that the entire satellite period is divided into different sub-periods according to certain specific requirements. The specific requirements here must include the start time, end time, and sub-period properties. For example, the circle number division method divides sub-periods according to the time of the satellite orbit circle point, and the shadow and sun zone division sub-periods according to the time of the time zone separation point. The comprehensive division method combines the sliding division and designated time division methods in a sequential order.

[0036] Sliding partitioning method Figure 3 As shown in FIG, the sliding division method starts from an arbitrary time starting point on the entire time axis and calculates the end time with a certain time length.

[0037] The steps for sliding sub-periods are as follows:

[0038] ① Arrange the satellite payload actions in ascending order according to the start time of the action;

[0039] ② Get the load action with the earliest start time in the queue and set its start time as T 10 , the end time is T 11 ;

[0040] ③ Get the sub-period of this sliding (conduct constraint check within the sub-period), whose start time is T 1S =T 10 , the end time is T 1E =T 10 +L;

[0041] ④ Find the first load action in the queue that is not included in the above sub-period, and set its start time as T 20 , the end time is T 21 ;

[0042] ⑤ Let ΔT = T 20 -T 1E ; If ΔT≥(T 11 -T 10 ), then go to step ⑦;

[0043] ⑥ Get a new sliding sub-period (to perform constraint checks within the sub-period), whose start time is T 2S =T 10 +ΔT, end time is T 2E =T 2S +L;

[0044] ⑦Remove the first item from the queue. If the queue is not empty, return to step ②.

[0045] Specify the time division method as follows Figure 4 As shown, the specified time division method clearly sets the division points of the sub-periods, and the start and end times of the corresponding sub-periods can be obtained according to the division points.

[0046] To specify a time period and divide it into sub-periods, follow these steps:

[0047] ① Arrange the sub-period separation points in ascending order of time;

[0048] ② Get the first time T0 and the second time T1 in the queue;

[0049] ③ Get the sub-period (conduct constraint check within the sub-period), whose start time is T S =T0, end time is T E =T1;

[0050] ④Remove the first moment in the queue. If the number of queues is greater than or equal to 2, return to step ②, otherwise end.

[0051] The comprehensive division method is a comprehensive application of the sliding division sub-period and the specified time division sub-period.

[0052] c) Satellite payload action condition result configuration

[0053] Satellite payload action conditional result configuration achieves a specific result by setting a number of conditions. When determining the conditional result, the payload action parameters are used as input, and numerical calculations, range determinations, enumerations, and text approximations are used to determine whether the input meets the conditions set for each satellite. If the conditions are met, the corresponding result is obtained. The result also uses the payload action parameters as input and is calculated according to the expressions given for each satellite to obtain the corresponding value.

[0054] d) Initial value setting, iteration and judgment of constraint items within sub-periods

[0055] Set constraints and initial values ​​for each sub-period, and then obtain the result items that meet the conditions within the sub-period according to the sub-period division principle, add the results to the initial values ​​of the constraints, and thus obtain the iterative results of the constraints. Compare the iterative results with the constraints to determine whether the constraints are met.

[0056] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Those skilled in the art can make some simple modifications, equivalent changes or modifications based on the technical content disclosed above, which all fall within the scope of protection of the present invention.

Claims

1. A general satellite payload energy constraint verification method, characterized in that: include: The satellite working time is divided into different satellite sub-periods, including: According to the sliding division method, the specified time division method, or the comprehensive division method, the satellite working time is divided into different satellite sub-periods, including: Step 1: Arrange the satellite payload actions in ascending order according to the start time of the action; Step 2: Get the load action with the earliest start time in the queue and set its start time as T 10 , the end time is T 11 ; Step 3: Get the sub-period of this sliding and perform constraint check within the sub-period, whose start time is T 1S =T 10 , the end time is T 1E =T 10 +L; Step 4: Find the first load action in the queue that is not included in the above sub-period, and set its start time as T 20 , the end time is T 21 ; Step 5: Let ΔT = T 20 -T 1E , if ΔT≥(T 11 -T 10 ), then jump to step 7; Step 6: Get a new sliding sub-period, whose start time is T 2S =T 10 +ΔT, end time is T 2E =T 2S +L; Step 7: Remove the first item from the queue. If the queue is not empty, return to step 2. According to the divided satellite sub-periods, the satellite payload action condition result configuration is executed; According to the configuration of the payload action condition results in each satellite sub-period, the constraint item test is performed in each satellite sub-period.

2. The general satellite payload energy constraint verification method according to claim 1, characterized in that: Also includes: Before dividing the satellite working time into different satellite sub-periods, the payload action queue is pre-processed.

3. The general satellite payload energy constraint verification method according to claim 2, characterized in that: Payload action queue preprocessing, including: Combine related load actions.

4. The general satellite payload energy constraint verification method according to claim 1, characterized in that: The designated time division methods include: circle number division method and shadow area and sun area division method.

5. The general satellite payload energy constraint verification method according to claim 1, characterized in that: According to the designated time division method, the satellite working time is divided into different satellite sub-periods, including: Step 1: Arrange the sub-period separation points in ascending order of time; Step 2: Get the first time T0 and the second time T1 in the queue; Step 3: Get the sub-period, whose start time is T S =T0, end time is T E =T1; Step 4: Remove the first moment in the queue. If the number of queues is greater than or equal to 2, return to step 2, otherwise end.

6. A universal satellite payload energy constraint test device, characterized in that: include: one or more processors; a storage device for storing one or more programs, When the one or more programs are executed by the one or more processors, the one or more processors implement the general satellite payload energy constraint verification method according to any one of claims 1 to 5.

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