Window calculation method based on remote sensing satellite inertial space shooting requirements

Abstract

The invention relates to a window calculation method based on a remote sensing satellite inertial space type shooting demand, relates to the technical field of remote sensing satellite task planning application, and solves the technical problems that the calculation process of the inertial space type satellite shooting demand in the prior art is complex in design, more in human intervention content and easy to cause operation errors in intermediate links. The method comprises the steps that a task planning system adds a mark which is not automatically calculated for an inertial space type demand of an uncalculated window, screening and aggregation scheduling are carried out, and calculation is carried out. According to the method, normal reception of inertial space requirements can be ensured, and the operation of the whole process and other subsystems is not affected; the automatic operation degree of the system can be improved, automatic calculation of windows of the requirements is carried out, manual filling of relevant parameters of shooting tasks is changed into automatic assignment when the requirements are reported, manual operation in the link is reduced, the process is simplified, and meanwhile the use efficiency of the whole system can be improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of remote sensing satellite mission planning application, and in particular to a window calculation method based on inertial space photographing demand of remote sensing satellites. BACKGROUND

[0002] In recent years, the hardware level of remote sensing satellites has been continuously improved, and the application target has higher requirements. The increasing number of satellites leads to more diversified satellite mission types and rapid growth in the number of target observation requirements. Although traditional ground-based in-orbit target photography is mature in technology, it often has low flexibility and imaging effects are easily affected. In contrast, space-based target observation has the advantages of wide detection range and strong maneuvering flexibility. However, for space-based photographing targets, the calculation of inertial space satellite photographing requirements has problems such as multiple calculation parameters and complex calculation process. Under the premise of ensuring correct and complete execution of the photographing task, compared with the automatic calculation of the visible window of the ground-based target task, the inertial space class demand needs to be calculated by technical personnel in advance, and then a large number of related parameters are manually filled in and associated with the photographing demand. Only then can the system generate a visible window according to the submitted parameters. This results in a complex overall process design and a lot of human intervention, and operation errors are likely to occur in the intermediate links. In addition, since the calculation of the visible window for inertial space photographing requirements is time-consuming, the related external interfaces and overall planning process will be delayed in terms of timing. Therefore, under higher conditions, the existing system design cannot meet the intelligent processing of this type of photographing demand. SUMMARY

[0003] The present application solves the technical problems of complex calculation process design, more human intervention, and operation errors in the intermediate links of inertial space satellite photographing requirements in the prior art, and provides a window calculation method based on inertial space photographing demand of remote sensing satellites.

[0004] To solve the above technical problems, the technical solution of the present application is as follows:

[0005] A window calculation method based on inertial space photographing demand of remote sensing satellites, comprising the following steps:

[0006] Step S1: After receiving the inertial space photographing demand, the task planning system adds a non-automatic calculation mark to the inertial space demand without calculating the window, and normally feeds back the related return value to other systems to ensure the normal operation of the overall process and the continuity of the task;

[0007] Step S2: The task planning system periodically selects and aggregates the inertial space requirements with the non-automatic calculation mark in the task pool through the asynchronous scheduling module, and sends the data request package of the related information of the photographing demand to the related calculation node for calculation.

[0008] Step S3: After receiving the call request, the external computing program package performs structural preprocessing and legality verification on the input demand information and inputs it into the algorithm, and sends the calculation result to the task planning system after being uniformly packaged;

[0009] Step S4: After receiving the return value of the external computing program, the task planning system matches the demand ID in the return value with the demand, and generates the visible window information of the shooting demand and the related parameters for executing the task according to the calculated parameter information;

[0010] Step S5: After generating the visible window, the task planning system changes the uncalculated mark in the shooting demand to a calculated mark.

[0011] In the above technical solution, step S1 is specifically: after receiving the inertial space shooting demand r through the external interface, first adding an uncalculated mark to the shooting demand r and storing it in the database; then adding the inertial space shooting demand r to the to-be-processed queue q; at the same time, the task planning system feeds back the demand receiving step to other systems related return value to ensure the normal operation of the overall process and the continuity of the task, and realizes the decoupling of the task process and the calculation delay process.

[0012] In the above technical solution, step S2 is specifically: the task planning system starts a timing program for screening and aggregation scheduling, and periodically retrieves all inertial space demands with uncalculated marks in the to-be-processed queue q. When the shooting demand r is retrieved, the external computing program j deployed on the server B is called through WebService, and the inertial space shooting demand r related information, related calculation parameters and integral step data are sent to the computing node j'; at the same time, the inertial space shooting demand r is discharged to the outside of the to-be-processed queue q; through the timed event-driven scheduling, the calculation task and the system management are decoupled.

[0013] In the above technical solution, in step S2, the shooting demand r related information includes: demand ID, demand start and end time, satellite and orbit information.

[0014] In the above technical solution, in step S2, the inertial space related calculation parameters include: satellite maneuvering time, solar elevation angle and maximum angular velocity.

[0015] In the above technical solution, step S3 is specifically: after receiving the call request, the external computing program j performs structural preprocessing and legality verification on the related information of the inertial space shooting demand r, and inputs it into the calculation algorithm. The output data of the calculated inertial space shooting demand r and the necessary task parameters for executing the inertial space are fed back to the task planning system as the return value of the interface.

[0016] In the technical solution, the output data of the inertial space type shooting demand r in step S3 includes a demand id of the inertial space type shooting demand r, a visible time, a frame period and an angular velocity.

[0017] In the technical solution, after the task planning system receives the output data of the inertial space type shooting demand r calculated by the external computing program j, the demand ID in the returned data is matched with the inertial space type shooting demand r, and the corresponding visible window information of the shooting demand r is generated according to the calculated parameter information, and the related parameters for executing the task are assigned, and the automatic window calculation of the inertial space type shooting demand r is completed.

[0018] The method has the following advantages:

[0019] The window calculation method based on the inertial space type shooting demand of a remote sensing satellite of the application changes the sequential and serial processing of the shooting demand and the visible window calculation process in the original process into asynchronous and delayed processing of the window, and introduces a task state sensing mechanism, which can ensure the normal reception of the inertial space type demand, does not affect the operation of the overall process and other subsystems, improves the degree of automatic operation of the system itself, performs automatic calculation of the window of the demand, and changes the manual filling of the related parameters of the shooting task into automatic assignment, reduces the manual operation in this link, simplifies the process, and improves the use efficiency of the overall system; the distributed design is adopted in the architecture, and the system and the computing service are separated to ensure the maximum efficiency of the computing service.

[0020] The window calculation method based on the inertial space type shooting demand of a remote sensing satellite of the application separates the inertial space type demand reporting from the inertial space type window automatic calculation step, and the operation steps are the same as other conventional task processing methods. BRIEF DESCRIPTION OF DRAWINGS

[0021] The application will be further described in detail below with reference to the drawings and specific embodiments.

[0022] Figure 1 The figure is a flowchart of the window calculation method based on the inertial space type shooting demand of a remote sensing satellite of the application.

[0023] Figure 2 The figure is a system architecture diagram suitable for the window calculation method based on the inertial space type shooting demand of a remote sensing satellite of the application. DETAILED DESCRIPTION

[0024] The inventive idea of the present application is:

[0025] Since the system receiving inertia space demand and window calculation operation have strong correlation in the existing process design, and the system does not have autonomous calculation capability for inertia space type window, the key to solving the problem lies in decoupling the receiving demand and the automatic visible window calculation two actions. The present application transforms the sequence serial processing of shooting demand and visible window calculation process in the original process into asynchronous delayed processing window, and introduces a task state sensing mechanism. This design can not only ensure the normal reception of inertia space type demand, without affecting the operation of the overall process and other subsystems, but also improve the degree of automation of the system itself, perform automatic calculation of the window of this type of demand, and change the manual filling of related parameters of the shooting task when the demand is submitted to automatic assignment, reducing the manual operation in this link, simplifying the process while improving the overall system efficiency. At the same time, the distributed design is adopted in the architecture, separating the system and the calculation service to ensure the maximum efficiency of the calculation service.

[0026] The window calculation method for inertia space type shooting demand of remote sensing satellite based on the present application separates the inertia space type demand submission from the inertia space type window automatic calculation, and the operation steps are the same as other conventional task processing methods.

[0027] The following will be combined Figure 1 ( Figure 1 only show the steps of the method of the present application) and Figure 2 The window calculation method for inertia space type shooting demand of remote sensing satellite based on the present application will be described in detail.

[0028] The window calculation method for inertia space type shooting demand of remote sensing satellite based on the present application comprises the following steps:

[0029] Step S1: Compared with the original process in which the parameters are filled manually before the demand submission, the improved process first introduces a task classification marking mechanism after receiving the inertia space type shooting demand. The task planning system adds a "not automatically calculated" mark to the inertia space type demand without window calculation, and normally feeds back to other system related return values to ensure the normal operation of the overall process and the continuity of the task.

[0030] Step S2: To address the issue of excessive computation time, the task planning system incorporates an asynchronous scheduling module. This module periodically filters and aggregates all inertial space requirements marked "not automatically calculated" in the task pool, and sends data request packets related to inertial space photography requirements to relevant computing nodes for computation.

[0031] Step S3: After receiving the call request, the external computing package performs structural preprocessing and legality verification on the input requirement information and inputs it into the algorithm. After packaging the calculation results, it sends them to the task planning system.

[0032] Step S4: After receiving the return value calculated by the external program, the task planning system matches the requirement ID in the return value with the requirement, and generates the visible window information of this type of shooting requirement and the relevant parameters for executing the task based on the calculated parameter information; relative to the manual filling of window parameters, this step realizes the automatic reconstruction of the shooting window and is compatible with subsequent processes;

[0033] Step S5: Introduce a closed-loop management mechanism. After generating the visible window, the task planning system will change the "not automatically calculated" mark in this type of shooting requirement to "calculated mark". The subsequent system scheduling module will no longer process requirements with this mark during retrieval, thus avoiding duplicate calculation.

[0034] The following section provides a detailed description of each step in the window calculation method based on the spatial imaging requirements of remote sensing satellites according to the present invention.

[0035] Regarding step S1, compared to the original process where parameters had to be manually entered before a request could be submitted, the improved process first initializes the task classification and marking mechanism: After receiving an inertial space-type photography request r through an external interface, the task planning system deployed on server A processes it differently than a regular photography request that immediately performs automatic window calculation upon entering the planning system; first, it adds a "not automatically calculated" mark to this type of photography request r and stores it in the database, then adds the inertial space-type photography request r to the pending queue q. Simultaneously, the task planning system normally feeds back the request reception step to other systems with relevant return values ​​to ensure the overall process runs normally and the continuity of tasks, thus decoupling the task flow from the calculation delay process.

[0036] To address the issue of excessive computation time in step S2, the task planning system incorporates an asynchronous scheduling module. The system initiates a timed program for filtering and aggregation scheduling, periodically searching the waiting queue q for all inertial space requirements marked "not automatically calculated." When an inertial space imaging requirement r is found, an external computing program j deployed on server B is invoked via a WebService. The program sends relevant information about the inertial space imaging requirement r, including requirement ID, start and end times, satellite information, orbital information, and relevant calculation parameters, such as satellite maneuver time, solar altitude angle, maximum angular velocity, and integration step size, to computing node j'. Simultaneously, the inertial space imaging requirement r is removed from the waiting queue q. This timed event-driven scheduling decouples the computation task from system management.

[0037] Regarding step S3, after receiving the call request, the external computing program j performs structural preprocessing and validity verification on the relevant information of the inertial space class imaging requirement r, and then inputs it into the computing algorithm. The output data of the calculated inertial space class imaging requirement r includes the requirement ID, visibility time, frame period, angular velocity, and other information such as the necessary task parameters for executing the inertial space class imaging, which is fed back to the task planning system as the return value of the interface. This step separates the main system from the computing module, encapsulating the computing module into an independent computing unit, supporting modular deployment and hot deployment.

[0038] In the external computing node, taking the process of calculating satellite attitude as an example, in the J2000 coordinate system, let the satellite's position and velocity be R at time t. s (t), V s (t). The target position and velocity are R and R respectively. o (t), V o (t). Then the observation vector L(t) is defined as:

[0039] L(t) = R o (t)–R s (t)

[0040] The corresponding spatial distance D(t) is:

[0041] D(t)=||L(t)||

[0042] Target relative linear velocity V rel (t) is:

[0043] V rel (t)=V o (t)-V s (t)

[0044] Decompose it into components along the line of sight and their perpendicular components: then the normalized observation vector for:

[0045]

[0046] The projection of relative velocity V along the line of sight || (t)(radial component) is:

[0047]

[0048] The tangential component V of the target's lateral sliding in the field of view tan (t) is:

[0049]

[0050] The relative angular velocity ω of the target in the field of view obs for:

[0051]

[0052] Therefore, the Earth's angular diameter is β earth for:

[0053]

[0054] Among them, R earth Represents the Earth's radius;

[0055] Then we can obtain the angle β between the optical axis of the satellite lens and the geocentric direction when the satellite is taking pictures. earth_target :

[0056]

[0057] Therefore, the condition for the target to be visible is:

[0058]

[0059] If the satellite coordinate system is defined as follows: the camera optical axis is the Z-axis, the pitch axis is the Y-axis, and the yaw axis is the X-axis. At the imaging center moment, let the Z-axis point towards the target. To increase the tolerance for trajectory recursion errors in the target's vertical velocity direction, let the X-axis point towards the direction of the target's linear velocity relative to the satellite. Then the satellite attitude DCM(t) is:

[0060]

[0061] Regarding step S4, after completing step S3, the task planning system, upon receiving the output data of the inertial space-type shooting requirement r calculated by the external calculation program j, first matches the requirement ID in the returned data with the inertial space-type shooting requirement r, and generates the corresponding visible window information for the shooting requirement r based on the calculated parameter information, as well as assigning values ​​to the relevant parameters for executing the task. At this point, the automated window calculation for the inertial space-type shooting requirement r is completed. Compared to the original process of manually filling in the visible window parameters, this step realizes the automatic reconstruction of the shooting window and is compatible with subsequent processes.

[0062] For step S5, a closed-loop management mechanism is introduced. After completing step S4, the task planning system changes the "not automatically calculated" flag in the inertial space imaging request r to "calculated flag". The scheduler will then no longer process requests with this flag. This effectively avoids redundant calculations and improves overall system performance.

[0063] The window calculation method based on remote sensing satellite inertial space-type imaging requirements of this invention transforms the original sequential processing of imaging requirements and visible window calculation into asynchronous delayed window processing, and introduces a task status awareness mechanism. This ensures the normal reception of inertial space-type requirements without affecting the overall process and the operation of other subsystems. It can improve the system's own automation level, automatically calculate the window for this type of requirement, and automatically assign relevant parameters for the imaging task instead of manually filling them in when submitting the requirement, reducing manual operations in this step, simplifying the process and improving the overall system efficiency. In terms of architecture, it adopts a distributed design, separating the system from the computing service to ensure the maximum efficiency of the computing service.

[0064] The window calculation method based on remote sensing satellite inertial space-type imaging requirements of the present invention, after the inertial space-type requirement is reported and enters the system, does not perform the operation of calculating the visible window. Then, it generally calls an external program, records the output return value to generate the visible window and various parameters of related execution tasks, so as to separate the inertial space-type requirement reporting and the automated calculation step of the inertial space-type window, and the operation steps are the same as other conventional task processing methods.

[0065] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A window calculation method based on the requirements of remote sensing satellite inertial space-type imaging, characterized in that, Includes the following steps: Step S1: After receiving an inertial space shooting request, the task planning system adds a mark for inertial space requests with uncalculated windows that have not been automatically calculated, and feeds back the relevant return values ​​to other systems to ensure the normal operation of the overall process and the continuity of the task. Step S2: The task planning system uses the asynchronous scheduling module to periodically filter and aggregate all inertial space requirements in the task pool that have not been automatically calculated and marked, and sends data request packets related to shooting requirements to relevant computing nodes for calculation. Step S3: After receiving the call request, the external computing package performs structural preprocessing and legality verification on the input requirement information and inputs it into the algorithm. After packaging the calculation results, it sends them to the task planning system. Step S4: After receiving the return value from the external calculation program, the task planning system matches the requirement ID in the return value with the requirement, and generates the visible window information for this type of shooting requirement and the relevant parameters for executing the task based on the calculated parameter information; Step S5: After generating the visible window, the task planning system changes the added, non-automatically calculated markers in this type of shooting requirement to calculated markers.

2. The window calculation method based on remote sensing satellite inertial space-type imaging requirements according to claim 1, characterized in that, Step S1 is as follows: After receiving the inertial space type shooting request r through the external interface, firstly, a flag that is not automatically calculated is added to the shooting request r and stored in the database; then, the inertial space type shooting request r is added to the pending queue q; at the same time, the task planning system normally feeds back the request receiving step to other systems and ensures the normal operation of the overall process and the continuity of the task, thereby decoupling the task process from the calculation delay process.

3. The window calculation method based on remote sensing satellite inertial space-type imaging requirements according to claim 2, characterized in that, Step S2 specifically involves: The task planning system initiates a timed program to filter and aggregate scheduling, periodically searching the pending queue q for all inertial space requirements that have not been automatically calculated and marked. When an inertial space imaging requirement r is found, the system calls the external computing program j deployed on server B via WebService, and sends the relevant information, calculation parameters, and integral step size data of the inertial space imaging requirement r to the computing node j'. At the same time, the inertial space imaging requirement r is removed from the pending queue q. Through timed event-driven scheduling, the computing task is decoupled from system management.

4. The window calculation method based on remote sensing satellite inertial space-type imaging requirements according to claim 3, characterized in that, In step S2, the information related to the inertial space imaging request r includes: request ID, request start and end time, and imaging satellite and orbit information.

5. The window calculation method based on remote sensing satellite inertial space-type imaging requirements according to claim 3, characterized in that, In step S2, the relevant calculation parameters include: satellite maneuver time, solar altitude angle, and maximum angular velocity.

6. The window calculation method based on remote sensing satellite inertial space-type imaging requirements according to claim 3, characterized in that, Step S3 is as follows: After receiving the call request, the external calculation program j performs structural preprocessing and legality verification on the relevant information of the inertial space class imaging requirement r and inputs it into the calculation algorithm. The output data of the calculated inertial space class imaging requirement r and the necessary task parameters for executing the inertial space class are fed back to the task planning system as the return value of the interface.

7. The window calculation method based on remote sensing satellite inertial space-type imaging requirements according to claim 6, characterized in that, In step S3, the output data of the inertial space shooting requirement r includes: the requirement ID of the inertial space shooting requirement r, the visible time, the frame period, and the angular velocity.

8. The window calculation method based on remote sensing satellite inertial space-type imaging requirements according to claim 3, characterized in that, Step S4 is as follows: After receiving the output data of the inertial space type shooting requirement r calculated by the external calculation program j, the task planning system first matches the requirement ID in the returned data with the inertial space type shooting requirement r, and generates the corresponding visible window information of the shooting requirement r according to the calculated parameter information and assigns values ​​to the relevant parameters for executing the task. At this time, the automated window calculation of the inertial space type shooting requirement r is completed.

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