Creo-based satellite dynamic field-of-view interference checking method and system

Abstract

The invention provides a Creo-based satellite dynamic view field interference checking method and system, and the method comprises the steps: setting a movement mechanism corresponding to a dynamic view field in a satellite digital model, and carrying out the model setting of all mechanisms needing the dynamic view field analysis on the satellite digital model; setting an in-orbit motion range of the motion mechanism, a field of view needing dynamic interference inspection, a corresponding potential interference object and in-orbit motion track information of the motion mechanism; executing an on-orbit working condition of the movement mechanism; whether interference occurs in the process of executing the on-orbit working condition of the movement mechanism is judged, if yes, working condition execution is stopped, and on-orbit movement track information of the movement mechanism is returned after the satellite configuration, the mechanism layout or the view field range is adjusted; and if not, executing the working condition, and ending the dynamic interference check. Compared with traditional satellite field-of-view static interference check, the in-orbit working condition motion trail can be covered more finely, and meanwhile the influence of interference check beyond the working condition range on satellite configuration and layout is avoided.

Description

Technical Field

[0001] This invention relates to the field of digital prototype technology for spacecraft, and more specifically, to a method and system for satellite dynamic field-of-view interferometry inspection based on Creo. Background Technology

[0002] Currently, satellite platforms are developing towards lightweighting and miniaturization, which places increasingly higher demands on the single-unit layout of satellites with field-of-view obstruction requirements. The traditional static field-of-view interferometry method involves statically arraying the single-unit field-of-view models according to their movable range, and then manually checking the interferometry between the array's field-of-view models and the models of potential interfering objects. However, this traditional method has the following problems:

[0003] (1) The granularity of the field of view array is difficult to control. If the granularity is too large, it cannot cover the actual on-orbit motion range, while if the granularity is too small, it will place higher demands on the computer hardware.

[0004] (2) The field of view of the array may exceed the range of motion under actual on-orbit operation, especially under the condition of multi-mechanism coordinated motion. In this case, the static field of view interferometry method will impose additional constraints on the configuration and layout of the satellite, which is not conducive to the goal of satellite lightweighting and miniaturization.

[0005] Patent document CN106599415A discloses a digital prototype interference inspection method. This patent document focuses on a digital model interference inspection process in the field of helicopter digital prototypes, while the present invention focuses on a dynamic field of view interference inspection method in the field of spacecraft digital prototypes, based on actual on-orbit operating conditions.

[0006] Patent document CN106248026A discloses a method for interference inspection of the layout structure of a compact space in a launch vehicle segment. This patent document mainly improves the layout design of rocket segments, engines, and servo mechanisms. Patent document CN108733884A discloses a digital model dynamic interference inspection system and method, which describes the general process and function of a digital dynamic interference inspection system. This invention, however, optimizes the impact of dynamic field of view with satellite obstruction requirements on satellite configuration and layout.

[0007] Patent document CN107944104A discloses a Creo dynamic and static interferometry result rapid feedback system and method, including a static interferometry result rapid feedback subsystem and a dynamic interferometry result rapid feedback subsystem. The static interferometry result rapid feedback subsystem realizes automated rapid static interferometry based on the Creo model, while the dynamic interferometry result rapid feedback subsystem realizes dynamic interferometry based on the Creo model and provides result feedback. This document uses Creo interferometry functionality to construct a dynamic and static interferometry management system and records the interferometry results. However, the patent does not address the handling methods after interference occurs in specific satellite field-of-view dynamic interferometry scenarios. Summary of the Invention

[0008] In view of the deficiencies in the prior art, the purpose of this invention is to provide a satellite dynamic field of view interferometry inspection method and system based on Creo.

[0009] A satellite dynamic field-of-view interferometry method based on Creo, provided by the present invention, includes:

[0010] Step S1: Set the motion mechanism corresponding to the dynamic field of view in the satellite digital model, and set up the model for all mechanisms on the satellite digital model that need to be analyzed by dynamic field of view;

[0011] Step S2: Set the on-orbit movement range of the motion mechanism;

[0012] Step S3: Set the field of view and the corresponding potential interference objects for the dynamic interference check;

[0013] Step S4: Set the on-orbit motion trajectory information of the motion mechanism according to the on-orbit operating conditions;

[0014] Step S5: Perform on-orbit operation of the motion mechanism;

[0015] Step S6: Determine whether interference occurs during the execution of the on-orbit working condition of the motion mechanism. If yes, stop executing the working condition, adjust the satellite configuration, mechanism layout or field of view, and return to step S4. If no, execute the working condition and the dynamic interference check ends.

[0016] Preferably, in the mechanism model, the operating range of the mechanism is set by software limiting;

[0017] The setting of the on-orbit motion range of the motion mechanism can verify that the motion trajectory under on-orbit working conditions is within the motion range of the mechanism.

[0018] Preferably, step S3 includes selecting the model objects to be checked for interference on the satellite digital model, including entities or face groups, based on the current dynamic interference check conditions.

[0019] Preferably, the trajectory information includes discrete time and position information, a discrete sequence of mechanism rotation angles that change over time based on the satellite's on-orbit position, and linear interpolation between the discrete positions.

[0020] Preferably, the number of motion mechanisms for interference checks is determined by the current operating conditions;

[0021] Near the time and location of interference, the granularity of trajectory information is refined to find interference time and location information that meets the granularity requirements.

[0022] According to the present invention, a Creo-based satellite dynamic field-of-view interferometry system includes:

[0023] Module M1: Sets the motion mechanism corresponding to the dynamic field of view in the satellite digital model, and sets up the model for all mechanisms on the satellite digital model that need to be analyzed by dynamic field of view;

[0024] Module M2: Sets the on-orbit movement range of the motion mechanism;

[0025] Module M3: Set the field of view and the corresponding potential interference objects for which dynamic interference checks are required;

[0026] Module M4: Sets the on-orbit motion trajectory information of the motion mechanism according to the on-orbit operating conditions;

[0027] Module M5: Executes the on-orbit operating conditions of the motion mechanism;

[0028] Module M6: Determines whether interference occurs during the execution of the on-orbit operating condition of the motion mechanism. If so, it stops executing the operating condition, adjusts the satellite configuration, mechanism layout, or field of view, and then returns to Module M4. If not, it executes the operating condition, and the dynamic interference check ends.

[0029] Preferably, in the mechanism model, the operating range of the mechanism is set by software limiting;

[0030] The setting of the on-orbit motion range of the motion mechanism can verify that the motion trajectory under on-orbit working conditions is within the motion range of the mechanism.

[0031] Preferably, the module M3 includes selecting model objects, including entities or face groups, on the satellite digital model to be subjected to interferometry based on the current dynamic interferometry inspection conditions.

[0032] Preferably, the trajectory information includes discrete time and position information, a discrete sequence of mechanism rotation angles that change over time based on the satellite's on-orbit position, and linear interpolation between the discrete positions.

[0033] Preferably, the number of motion mechanisms for interference checks is determined by the current operating conditions;

[0034] Near the time and location of interference, the granularity of trajectory information is refined to find interference time and location information that meets the granularity requirements.

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] 1. In the satellite digital model, the present invention sets the motion mechanism and its motion range corresponding to the dynamic field of view, which can effectively verify that the motion trajectory under the on-orbit working condition is within the motion range of the mechanism.

[0037] 2. This invention sets up a field-of-view model and potential interference targets that need to be checked during on-orbit operation, avoiding time-consuming whole-satellite interference checks.

[0038] 3. Based on the on-orbit operating conditions, this invention sets the motion trajectory information of the dynamic field of view and uses linear difference between discrete position points, so that the interference inspection scenario is closer to the actual on-orbit motion conditions.

[0039] 4. This invention performs dynamic interference checks based on actual on-orbit operating condition information, avoiding excessive constraints on satellite configuration and layout beyond the actual on-orbit operating condition range, which is beneficial for the lightweight and miniaturized design of the satellite platform. Attached Figure Description

[0040] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0041] Figure 1 This is a schematic diagram of the working method of the present invention. Detailed Implementation

[0042] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0043] This invention defines the motion trajectory of the field-of-view model based on actual on-orbit motion conditions and automatically determines trajectory interference through a program. Compared to traditional static interferometry checks of satellite fields of view, it can more precisely cover the on-orbit motion trajectory while avoiding the impact of interferometry checks beyond the operational condition range on satellite configuration and layout.

[0044] Example 1

[0045] According to the present invention, a satellite dynamic field-of-view interferometry inspection method based on Creo is provided, such as... Figure 1 As shown, it includes:

[0046] Step S1: Set up the motion mechanisms corresponding to the dynamic field of view in the satellite digital model. Configure the models for all mechanisms on the satellite digital model that require dynamic field of view analysis. For example, during the assembly stage, the motion mechanisms are assembled using a "pin" method. In the Creo motion mechanism module, the assembled rotating mechanism is set to the "servo motor" attribute. The satellite digital model includes the Creo digital model.

[0047] Step S2: Set the on-orbit movement range of the motion mechanism. In the mechanism model, set the operating range of the mechanism limited by software. Setting the on-orbit movement range of the motion mechanism can verify that the motion trajectory under on-orbit conditions is within the range of motion of the mechanism. For example, in the assembly definition, set the zero position of the "pin" and set the range or angle of the mechanism's operation limited by the on-orbit control software.

[0048] Step S3: Set the field of view and corresponding potential interference objects for dynamic interferometry. Based on the current dynamic interferometry conditions, select the model objects to be interferogram-checked on the satellite digital model, such as the Creo motion mechanism module, including solids or surface groups. Setting the field of view and potential interference objects for interferometry avoids time-consuming whole-satellite interferometry and improves interferometry efficiency.

[0049] Step S4: Based on the on-orbit operating conditions, set the on-orbit motion trajectory information of the motion mechanism. The trajectory information includes discrete time and position information, a discrete sequence of mechanism rotation angles varying over time calculated based on the satellite's on-orbit position, and linear interpolation between discrete positions. The number of motion mechanisms subject to interference checks is determined by the current operating conditions. Near the time and location where interference exists, the granularity of the trajectory information is refined to find interference time and position information that meets the granularity requirements.

[0050] Step S5: Perform on-orbit operation of the motion mechanism.

[0051] Step S6: Determine whether interference occurs during the execution of the on-orbit working condition of the motion mechanism. If yes, stop executing the working condition, adjust the satellite configuration, mechanism layout or field of view, and return to step S4. If no, execute the working condition and the dynamic interference check ends.

[0052] This invention provides a satellite dynamic interferometry inspection method that performs dynamic interferometry inspection on the satellite's digital model under actual on-orbit conditions for fields of view with obstruction requirements. It provides closed-loop processing of interference problems by adjusting one or more of the following methods: satellite configuration, structural layout, or field of view range. This ensures that while handling satellite dynamic field of view interference problems, it avoids over-constraints on satellite configuration and layout caused by field of view interference exceeding the on-orbit operating conditions, thereby facilitating the lightweight and miniaturized design of the satellite.

[0053] Example 2

[0054] The present invention also provides a Creo-based satellite dynamic field-of-view interferometry inspection system, which can be implemented by executing the process steps of the Creo-based satellite dynamic field-of-view interferometry inspection method. That is, those skilled in the art can understand the Creo-based satellite dynamic field-of-view interferometry inspection method as a preferred embodiment of the Creo-based satellite dynamic field-of-view interferometry inspection system.

[0055] According to the present invention, a Creo-based satellite dynamic field-of-view interferometry inspection system includes: Module M1: setting the motion mechanisms corresponding to the dynamic field of view in the satellite digital model, and setting the models of all mechanisms on the satellite digital model that require dynamic field-of-view analysis. Module M2: setting the on-orbit motion range of the motion mechanisms. In the mechanism model, the operating range of the mechanism is set by software limits. Setting the on-orbit motion range of the motion mechanisms can verify that the motion trajectory under on-orbit conditions is within the movable range of the mechanism. Module M3: setting the field of view to be dynamically interferometrically inspected and the corresponding potential interference objects. Module M3 includes selecting the model objects to be interferometrically inspected on the satellite digital model according to the current dynamic interferometry inspection conditions, including solids or face groups. Module M4: setting the on-orbit motion trajectory information of the motion mechanisms according to the on-orbit conditions. The trajectory information includes discrete time and position information, a discrete sequence of mechanism rotation angles changing with time calculated based on the satellite's on-orbit position, and linear interpolation between discrete positions. The number of motion mechanisms to be interferometrically inspected is determined by the current operating conditions. Near the time and location of interference, the granularity of the trajectory information is refined to find interference time and location information that meets the granularity requirements. Module M5: Executes the on-orbit operating condition of the motion mechanism. Module M6: Determines whether interference occurs during the execution of the on-orbit operating condition of the motion mechanism. If so, the execution of the operating condition is stopped, and the satellite configuration, mechanism layout, or field of view is adjusted before returning to module M4. If not, the operating condition is executed, and the dynamic interference check ends.

[0056] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0057] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A satellite dynamic field-of-view interferometry inspection method based on Creo, characterized in that, include: Step S1: Set the motion mechanism corresponding to the dynamic field of view in the satellite digital model, and set up the model for all mechanisms on the satellite digital model that need to be analyzed by dynamic field of view; Step S2: Set the on-orbit movement range of the motion mechanism; Step S3: Set the field of view and the corresponding potential interference objects for the dynamic interference check; Step S4: Set the on-orbit motion trajectory information of the motion mechanism according to the on-orbit operating conditions; Step S5: Perform on-orbit operation of the motion mechanism; Step S6: Determine whether interference occurs during the execution of the on-orbit working condition of the motion mechanism. If yes, stop executing the working condition, adjust the satellite configuration, mechanism layout or field of view, and return to step S4. If no, execute the working condition and the dynamic interference check ends.

2. The satellite dynamic field-of-view interferometry inspection method based on Creo according to claim 1, characterized in that, In the mechanism model, the operating range of the mechanism is set by software limits; The setting of the on-orbit motion range of the motion mechanism can verify that the motion trajectory under on-orbit working conditions is within the motion range of the mechanism.

3. The satellite dynamic field-of-view interferometry inspection method based on Creo according to claim 1, characterized in that, Step S3 includes selecting the model objects to be checked for interference on the satellite digital model, including entities or face groups, based on the current dynamic interference check conditions.

4. The satellite dynamic field-of-view interferometry inspection method based on Creo according to claim 1, characterized in that, The trajectory information includes discrete time and position information, a discrete sequence of mechanism rotation angles that change over time based on the satellite's on-orbit position, and linear interpolation between discrete positions.

5. The satellite dynamic field-of-view interferometry inspection method based on Creo according to claim 1, characterized in that, The number of motion mechanisms subject to interference checks is determined by the current operating conditions; Near the time and location of interference, the granularity of trajectory information is refined to find interference time and location information that meets the granularity requirements.

6. A satellite dynamic field-of-view interferometry inspection system based on Creo, characterized in that, include: Module M1: Sets the motion mechanism corresponding to the dynamic field of view in the satellite digital model, and sets up the model for all mechanisms on the satellite digital model that need to be analyzed by dynamic field of view; Module M2: Sets the on-orbit movement range of the motion mechanism; Module M3: Set the field of view and the corresponding potential interference objects for which dynamic interference checks are required; Module M4: Sets the on-orbit motion trajectory information of the motion mechanism according to the on-orbit operating conditions; Module M5: Executes the on-orbit operating conditions of the motion mechanism; Module M6: Determines whether interference occurs during the execution of the on-orbit operating condition of the motion mechanism. If so, it stops executing the operating condition, adjusts the satellite configuration, mechanism layout, or field of view, and then returns to Module M4. If not, it executes the operating condition, and the dynamic interference check ends.

7. The Creo-based satellite dynamic field-of-view interferometry inspection system according to claim 6, characterized in that, In the mechanism model, the operating range of the mechanism is set by software limits; The setting of the on-orbit motion range of the motion mechanism can verify that the motion trajectory under on-orbit working conditions is within the motion range of the mechanism.

8. The Creo-based satellite dynamic field-of-view interferometry inspection system according to claim 6, characterized in that, The module M3 includes selecting model objects, including entities or face groups, that need to be checked on the satellite digital model based on the current dynamic interferometry check conditions.

9. The Creo-based satellite dynamic field-of-view interferometry inspection system according to claim 6, characterized in that, The trajectory information includes discrete time and position information, a discrete sequence of mechanism rotation angles that change over time based on the satellite's on-orbit position, and linear interpolation between discrete positions.

10. The Creo-based satellite dynamic field-of-view interferometry inspection system according to claim 6, characterized in that, The number of motion mechanisms subject to interference checks is determined by the current operating conditions; Near the time and location of interference, the granularity of trajectory information is refined to find interference time and location information that meets the granularity requirements.

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