Conflict detection method and device for aerospace measurement and control resource allocation

Abstract

The present invention discloses a conflict detection method and device for aerospace measurement and control resource allocation. The method includes: determining a first measurement and control parameter of a measurement and control device, and a second measurement and control parameter corresponding to a plurality of spacecraft supported by the measurement and control device, the measurement and control device is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; obtaining a plurality of measurement and control projects of a plurality of spacecraft to obtain a measurement and control project set; and detecting the measurement and control project set according to preset constraints, the first measurement and control parameter and the second measurement and control parameter. The present invention solves the technical problem in the related art that a plurality of spacecraft are in parallel at the same time, and their measurement and control resources are prone to conflict. At present, only the method of detecting the conflict of the support capability of the number of uplink targets is performed, which has poor flexibility and is difficult to meet the needs.

Description

Technical Field

[0001] The present invention relates to the field of aerospace testing, and in particular to a method and device for conflict detection in aerospace measurement and control resource allocation. Background Art

[0002] The flight control of on-orbit spacecraft needs to complete tasks such as downlink data reception, uplink remote control injection, distance measurement, and speed measurement with the support of multiple measurement and control resources. The complexity of current space missions is gradually increasing, and it is becoming more and more common for multiple spacecraft to share multiple ground measurement and control networks and space-based relay satellites to complete measurement and control tasks. It is also becoming more and more common for a single set of measurement and control equipment to support the measurement and control of multiple spacecraft targets. In addition, multiple spacecraft have multiple combination modes such as individual flight, formation flight, and combined operation. Different modes have different joint use modes of ground-based measurement and control resources.

[0003] In order to make full use of ground measurement and control resources, the mission center adopts the strategy of using multiple sets of space-based measurement and control equipment to simultaneously complete the measurement and control tasks of multiple spacecraft. The measurement and control resource allocation of different spacecraft is often designed by different flight control users. Therefore, there is a high possibility of conflict in the space measurement and control resource allocation results of different flight control users. In order to avoid measurement and control resource allocation conflicts, the current conflict detection method is to only perform conflict detection on the limit of the number of uplink support targets set for all measurement and control equipment. It does not distinguish between measurement and control equipment, and does not distinguish between uplink and downlink measurement and control capabilities. It is impossible to implement targeted conflict detection based on the uplink and downlink support capabilities of different measurement and control equipment and equipment.

[0004] To address the above-mentioned problems, no effective solution has been proposed yet. Summary of the invention

[0005] The embodiments of the present invention provide a method and device for conflict detection in aerospace tracking and control resource allocation, so as to at least solve the technical problem in the related technology that multiple spacecraft are operating in parallel at the same time, and their tracking and control resources are prone to conflicts. Currently, only the method of detecting conflicts in the support capability of the number of uplink targets is performed, which has poor flexibility and is difficult to meet the needs.

[0006] According to one aspect of an embodiment of the present invention, a conflict detection method for aerospace measurement and control resource allocation is provided, comprising: determining a first measurement and control parameter of a measurement and control device, and a second measurement and control parameter corresponding to a plurality of spacecraft supported by the measurement and control device, wherein the measurement and control device is used to provide measurement and control resources for the plurality of supported spacecraft, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; acquiring a plurality of measurement and control items of the plurality of spacecraft to obtain a measurement and control item set; and detecting the measurement and control item set according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, wherein the constraints include a plurality of constraints on the measurement and control device, the spacecraft, or data transmission between the measurement and control device and the spacecraft.

[0007] Optionally, determining the first measurement and control parameters of the measurement and control device, and the second measurement and control parameters corresponding to the multiple spacecraft supported by the measurement and control device includes: obtaining a resource file in a first preset format of the measurement and control device based on the first device identifier of the measurement and control device, wherein the resource file includes the first device identifier of the measurement and control device and the first measurement and control parameter; and obtaining requirement files in a second preset format of the multiple spacecraft based on the second device identifier of the spacecraft, wherein the requirement files include the second device identifier of the corresponding spacecraft, and the second measurement and control parameter.

[0008] Optionally, the first measurement and control parameters include at least one of the following: a downlink measurement and control point frequency support capability parameter, the number of spacecraft supported simultaneously in the downlink, an uplink measurement and control point frequency support capability parameter, the number of spacecraft supported simultaneously in the uplink, and an uplink elevation angle constraint parameter; the second measurement and control parameters include at least one of the following: a downlink measurement and control point frequency support capability parameter, the number of point frequencies supported simultaneously in the downlink, an uplink measurement and control point frequency support capability parameter, the number of measurement and control devices supported simultaneously in the uplink, and a ground-based measurement and control support capability parameter.

[0009] Optionally, the measurement and control project corresponds to an identifier of the equipment or data involved in the project, and measurement and control project parameters between the measurement and control equipment and the spacecraft corresponding to the measurement and control project; the identifier includes at least one of the following: an allocation identifier, a first equipment identifier, a second equipment identifier; the measurement and control project parameters include at least one of the following: the start time and end time of the measurement and control equipment tracking the corresponding spacecraft in the measurement and control project; the uplink start time, uplink end time, downlink start time and downlink end time between the measurement and control equipment and the corresponding spacecraft; the uplink point frequency and downlink point frequency between the measurement and control equipment and the spacecraft corresponding to the measurement and control equipment.

[0010] Optionally, according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, before detecting the measurement and control project set, also include: obtaining multiple preset constraints, wherein each constraint includes at least a constraint object and a constraint behavior; storing the multiple constraints in a target rule stack according to the order in which the constraint objects targeted by the multiple constraints execute corresponding constraint behaviors in the measurement and control projects.

[0011] Optionally, according to preset constraints, the first measurement and control parameters and the second measurement and control parameters, the detection of the measurement and control project set includes: selecting the first measurement and control project in the measurement and control project set according to a preset order; according to multiple constraints in the target rule stack, in the order of precedence, respectively detecting whether the constraint behavior of the constraint object of the measurement and control project satisfies the corresponding constraint; when the measurement and control project passes the detection of all constraints in the target rule stack, detecting the execution parameters of the measurement and control equipment of the measurement and control project according to the first measurement and control parameters, and detecting the execution parameters of the spacecraft of the measurement and control project according to the second measurement and control parameters; when the measurement and control project passes the first measurement and control parameters and the second measurement and control parameters, determining that the measurement and control project passes the detection; selecting the next measurement and control project from the measurement and control project set in the preset order for detection until all measurement and control projects in the measurement and control project set have completed the detection.

[0012] Optionally, the multiple constraints include: a switching time constraint of the measurement and control equipment, wherein the switching time constraint includes the equipment identification of the measurement and control equipment, and the switching time threshold of the measurement and control equipment for tracking a spacecraft twice; a first constraint on the number of spacecraft tracked simultaneously by the measurement and control equipment, wherein the first constraint includes the identification of the measurement and control equipment, and the maximum number of spacecraft tracked simultaneously by the measurement and control equipment; a second constraint on the number of spacecraft simultaneously uplinked by the measurement and control equipment, wherein the second constraint includes the identification of the measurement and control equipment, and the maximum number of spacecraft simultaneously uplinked by the measurement and control equipment; a third constraint on the number of spacecraft simultaneously downlinked by the measurement and control equipment, wherein the third constraint includes the identification of the measurement and control equipment, and the maximum number of spacecraft simultaneously downlinked by the measurement and control equipment; a fourth constraint on the number of links simultaneously uplinked by the measurement and control equipment, wherein the fourth constraint includes the identification of the measurement and control equipment, and the maximum number of links simultaneously uplinked by the measurement and control equipment.

[0013] Optionally, according to preset constraints, after the first measurement and control parameters and the second measurement and control parameters detect the set of measurement and control items, the method also includes: recording the detection results one by one and generating a detection report; marking illegal measurement and control items in the detection results as illegal measurement and control items.

[0014] According to another aspect of an embodiment of the present invention, a conflict detection device for aerospace measurement and control resource allocation is also provided, including: a determination module, used to determine a first measurement and control parameter of a measurement and control device, and a second measurement and control parameter corresponding to a plurality of spacecraft supported by the measurement and control device, wherein the measurement and control device is used to provide measurement and control resources for the plurality of supported spacecraft, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; an acquisition module, used to acquire a plurality of measurement and control items of the plurality of spacecraft to obtain a set of measurement and control items; a detection module, used to detect the set of measurement and control items according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, wherein the constraints include a plurality of constraints on the measurement and control device, the spacecraft, or data transmission between the measurement and control device and the spacecraft.

[0015] According to another aspect of an embodiment of the present invention, a processor is further provided, wherein the processor is used to run a program, wherein when the program is run, any one of the above-mentioned conflict detection methods for aerospace tracking and control resource allocation is executed.

[0016] According to another aspect of an embodiment of the present invention, a computer storage medium is further provided, wherein the computer storage medium includes a stored program, wherein when the program is running, the device where the computer storage medium is located is controlled to execute any one of the above-mentioned conflict detection methods for the allocation of aerospace measurement and control resources.

[0017] In an embodiment of the present invention, a first measurement and control parameter of a measurement and control device and second measurement and control parameters corresponding to a plurality of spacecraft supported by the measurement and control device are determined, wherein the measurement and control device is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; a plurality of measurement and control items of the plurality of spacecraft are obtained to obtain a measurement and control item set; the measurement and control item set is detected according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, wherein the constraints include a plurality of constraints on the measurement and control device, the spacecraft or the data transmission between the measurement and control device and the spacecraft, and the measurement and control item set is detected by the preset constraints, the first measurement and control parameter and the second measurement and control parameter, so as to achieve the purpose of setting the measurement and control item set by setting the constraints according to the requirements, thereby achieving the technical effect of improving the flexibility of the measurement and control item detection and detecting the measurement and control item set according to the requirements, thereby solving the technical problem that in the related technology, when multiple spacecraft are in parallel at the same time, the measurement and control resources are prone to conflict, and the current method of only detecting the conflict of the support capability of the number of uplink targets is poor in flexibility and difficult to meet the requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0019] Figure 1 is a flow chart of a method for conflict detection of aerospace tracking and control resource allocation according to an embodiment of the present invention;

[0020] Figure 2 is a schematic diagram of capability parameters of a measurement and control device according to an embodiment of the present invention;

[0021] Figure 3 is a schematic diagram of capability parameters of a spacecraft according to an embodiment of the present invention;

[0022] Figure 4 It is a schematic diagram of a conflict detection device for aerospace tracking and control resource allocation according to an embodiment of the present invention. DETAILED DESCRIPTION

[0023] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0024] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0025] According to an embodiment of the present invention, a method embodiment of a conflict detection method for aerospace measurement and control resource allocation is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0026] Figure 1 FIG. 1 is a flow chart of a method for detecting conflicts in aerospace tracking and control resource allocation according to an embodiment of the present invention. Figure 1 As shown, the method comprises the following steps:

[0027] Step S102, determining a first measurement and control parameter of the measurement and control device, and second measurement and control parameters corresponding to a plurality of spacecraft supported by the measurement and control device, wherein the measurement and control device is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft;

[0028] Step S104, acquiring multiple measurement and control items of multiple spacecraft to obtain a measurement and control item set;

[0029] Step S106, detecting the measurement and control item set according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, wherein the constraints include multiple constraints on the measurement and control equipment, the spacecraft or the data transmission between the measurement and control equipment and the spacecraft.

[0030] Through the above steps, a first measurement and control parameter of the measurement and control device and a second measurement and control parameter corresponding to a plurality of spacecraft supported by the measurement and control device are determined, wherein the measurement and control device is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; a plurality of measurement and control items of the plurality of spacecraft are obtained to obtain a measurement and control item set; the measurement and control item set is detected according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, wherein the constraints include a plurality of constraints on the measurement and control device, the spacecraft or the data transmission between the measurement and control device and the spacecraft, and the measurement and control item set is detected by the preset constraints, the first measurement and control parameter and the second measurement and control parameter, so as to achieve the purpose of setting the measurement and control item set by setting the constraints according to the requirements, thereby achieving the technical effect of improving the flexibility of the measurement and control item detection and detecting the measurement and control item set according to the requirements, thereby solving the technical problem that the measurement and control resources of the plurality of spacecrafts in parallel in the related technology are prone to conflict, and the current method of only detecting the conflict of the support capability of the number of uplink targets is poor in flexibility and difficult to meet the requirements.

[0031] The above-mentioned measurement and control equipment can be measurement and control equipment installed on the ground, and the spacecraft can be a spacecraft such as a spacecraft or a satellite. The flight control of the spacecraft has very high requirements for accuracy. It is necessary to obtain various data during the flight of the spacecraft in real time, and control the spacecraft according to the deviation between the actual position and the planned position. This process is measurement and control. With the development of aerospace technology, the measurement and control tasks of spacecraft are becoming more and more complex and diverse. Through the distribution of multiple measurement and control equipment on the ground, the measurement and control needs of multiple spacecraft are supported at the same time. That is, relative to one measurement and control equipment, it also supports multiple spacecraft. This embodiment takes one measurement and control equipment as an example, and the principles and steps of other measurement and control equipment are the same.

[0032] The above-mentioned first measurement and control parameters include at least one of the following: downlink measurement and control point frequency support capability parameter, the number of spacecraft supported simultaneously in the downlink, uplink measurement and control point frequency support capability parameter, the number of spacecraft supported simultaneously in the uplink, and uplink elevation angle constraint parameter; the second measurement and control parameters include at least one of the following: downlink measurement and control point frequency support capability parameter, the number of point frequencies supported simultaneously in the downlink, uplink measurement and control point frequency support capability parameter, the number of measurement and control devices supported simultaneously in the uplink, and ground-based measurement and control support capability parameter.

[0033] The first measurement and control parameter of the measurement and control equipment is the measurement and control capability parameter of the measurement and control equipment when supporting the spacecraft to perform measurement and control tasks, such as Figure 2 As shown, the first measurement and control parameter of the measurement and control equipment may include: a downlink measurement and control point frequency support capability parameter, that is, the point frequency range supported by the downlink communication between the measurement and control equipment and the spacecraft; the number of spacecraft supported simultaneously in the downlink, that is, the maximum number of spacecraft that can be simultaneously corresponded during the downlink process; an uplink measurement and control point frequency support capability parameter, that is, the point frequency range supported by the uplink communication between the measurement and control equipment and the spacecraft; the number of spacecraft supported simultaneously in the uplink, that is, the maximum number of spacecraft that the measurement and control equipment can simultaneously correspond to during the uplink process; an uplink elevation angle constraint parameter, that is, when the measurement and control equipment communicates uplink with the spacecraft, it is necessary to ensure that the elevation angle between the spacecraft and the measurement and control equipment meets a certain range. If the range is exceeded, the measurement and control equipment cannot communicate uplink with the spacecraft. The elevation angle constraint, that is, the elevation angle range of the spacecraft corresponding to the uplink communication of the measurement and control equipment.

[0034] The measurement and control capability of the measurement and control equipment can be clarified through the first measurement and control parameter. According to the measurement and control capability of the measurement and control equipment, partial data detection can be performed on the measurement and control project between the measurement and control equipment and the supported spacecraft. This partial data is also partial data related to the measurement and control equipment. For example, the number of spacecrafts supported by the uplink of the first measurement and control parameter of the measurement and control equipment is 5. In this measurement and control project, if the measurement and control equipment supports uplink communication of 6 spacecrafts at the same time, then there must be something wrong with this parameter, which cannot be realized and cannot pass the detection, and needs to be adjusted.

[0035] The above-mentioned uplink and downlink are based on the communication process between the measurement and control equipment and the spacecraft. Generally speaking, uplink communication is the measurement and control equipment sending data to the spacecraft, and downlink communication is the spacecraft sending data to the measurement and control equipment.

[0036] The second measurement and control parameter of the above-mentioned spacecraft is the measurement and control capability parameter of the measurement and control equipment when supporting the spacecraft to perform measurement and control tasks, such as Figure 3 As shown, the second measurement and control parameter of the spacecraft includes at least one of the following: a downlink measurement and control frequency support capability parameter, that is, the frequency range of the downlink communication supported between the spacecraft and the measurement and control equipment; the number of downlink frequency points supported simultaneously, that is, the maximum number of communication frequency points that the spacecraft can correspond to simultaneously during the downlink process, and different communication frequency points are used for downlink communication with different equipment, such as ground stations, measurement and control equipment, ground radar, etc.; an uplink measurement and control frequency support capability parameter, that is, the frequency range of the uplink communication supported between the spacecraft and the measurement and control equipment; the number of measurement and control equipment simultaneously supported in the uplink, that is, the maximum number of spacecraft that the measurement and control equipment can correspond to simultaneously during the uplink process; a space-ground based measurement and control support capability parameter, that is, the capability parameter of the spacecraft to perform uplink and downlink measurement and control data in a space-based or ground-based environment, including the frequency range, uplink and downlink communication time, the number of uplink and downlink simultaneously supported, etc.

[0037] The second measurement and control parameter can be used to clarify the measurement and control capability of the spacecraft. According to the measurement and control capability of the spacecraft, partial data detection can be performed on the measurement and control items between the measurement and control equipment and the supported spacecraft. This partial data is also partial data related to the spacecraft. For example, the number of measurement and control equipment supported by the uplink of the second measurement and control parameter of the spacecraft is 5. In this measurement and control project, if the spacecraft supports uplink communication of 6 measurement and control equipment at the same time, then there must be a problem with this parameter, which cannot be realized and needs to be adjusted through detection.

[0038] Acquire multiple measurement and control projects of multiple spacecraft to obtain a set of measurement and control projects. The above measurement and control project can be a specific part of a measurement and control task, or it can be the measurement and control task itself when the measurement and control task is relatively simple. A measurement and control project is actually a measurement and control process, which involves spacecraft, measurement and control equipment, and uplink and downlink communications between the spacecraft and the measurement and control equipment. That is, the measurement and control project includes the spacecraft to be executed, the measurement and control equipment that supports the spacecraft, and the uplink and downlink between the measurement and control equipment and the spacecraft.

[0039] The above measurement and control tasks or measurement and control projects can be designed by relevant designers according to the space mission of the spacecraft. The measurement and control tasks or measurement and control projects can be pre-designed and stored in relevant memory or database. During detection, the measurement and control tasks or measurement and control projects can be directly obtained by accessing the memory or database. Since the space flight process of the spacecraft requires multi-party collaboration, the measurement and control tasks and measurement and control projects are designed according to certain mission standards, and their parameters such as data format are implemented in accordance with the standards. Therefore, the measurement and control projects or measurement and control tasks of the spacecraft can be determined by direct acquisition and combined with the standards.

[0040] The above-mentioned measurement and control project corresponds to the identification of the equipment or data involved in the project, and the measurement and control project parameters between the measurement and control equipment and the spacecraft corresponding to the measurement and control project; the identification includes at least one of the following: an allocation identification, a first equipment identification of the measurement and control equipment, and a second equipment identification of the spacecraft; the measurement and control project parameters include at least one of the following: the start time and end time of the measurement and control equipment tracking the corresponding spacecraft in the measurement and control project; the uplink start time, uplink end time, downlink start time and downlink end time between the measurement and control equipment and the corresponding spacecraft; the uplink point frequency and downlink point frequency between the measurement and control equipment and the spacecraft corresponding to the measurement and control equipment.

[0041] Its measurement and control equipment tracks the start and end times of the corresponding spacecraft in the measurement and control project, and can determine whether the measurement and control equipment and the spacecraft meet the tracking requirements based on the first measurement and control parameters of the measurement and control equipment and the second measurement and control parameters of the spacecraft. The tracking of the spacecraft by the above-mentioned measurement and control equipment, that is, the process in which the measurement and control equipment can exchange data with the spacecraft through uplink and downlink communications. During the tracking process, it is necessary to ensure the uplink and downlink communications between the measurement and control equipment and the spacecraft. When the uplink constraints are met, the measurement and control equipment and the spacecraft can communicate effectively, that is, when the uplink communication is guaranteed, the downlink communication can also be carried out. On the contrary, if the uplink communication is not satisfied or the downlink communication is not satisfied, or both the uplink communication and the Xiaxin communication are not satisfied, the measurement and control equipment will naturally be unable to track the spacecraft.

[0042] The uplink start time, uplink end time, downlink start time and downlink end time; the uplink point frequency and downlink point frequency between the measurement and control equipment and the spacecraft corresponding to the measurement and control equipment, and other parameters can be determined and detected through one or more first measurement and control parameters and / or second measurement and control parameters.

[0043] Optionally, before testing the measurement and control project set according to the preset constraints, the first measurement and control parameters and the second measurement and control parameters, it also includes: obtaining multiple preset constraints, wherein each constraint includes at least a constraint object and a constraint behavior; storing the multiple constraints in a target rule stack according to the order in which the constraint objects targeted by the multiple constraints execute corresponding constraint behaviors in the measurement and control projects.

[0044] The above-mentioned multiple preset constraints can be multiple constraints determined by relevant inspection personnel according to inspection requirements. The above-mentioned measurement and control items need to meet all preset constraints to pass the inspection. The above-mentioned multiple constraints can be stored in the target rule stack, and can be read in the order of storage when reading, so as to realize the sequential reading of multiple constraints.

[0045] Optionally, testing the measurement and control project set according to preset constraints, first measurement and control parameters and second measurement and control parameters includes: selecting the first measurement and control project in the measurement and control project set according to a preset order; testing, in order of precedence, whether the constraint behavior of the constraint object of the measurement and control project satisfies the corresponding constraint conditions according to multiple constraints in the target rule stack; when the measurement and control project passes the test of all constraints in the target rule stack, testing the execution parameters of the measurement and control equipment of the measurement and control project according to the first measurement and control parameters, and testing the execution parameters of the spacecraft of the measurement and control project according to the second measurement and control parameters; when the measurement and control project passes the first measurement and control parameters and the second measurement and control parameters, determining that the measurement and control project passes the test; selecting the next measurement and control project from the measurement and control project set in the preset order for testing until all measurement and control projects in the measurement and control project set have completed the test.

[0046] During detection, the first measurement and control parameter and the second measurement and control parameter are detections of specific parameters, while the constraint conditions are for the specific behavior of a certain object. Specifically, the multiple constraints include at least one of the following: a switching time constraint of the measurement and control equipment, wherein the switching time constraint includes the equipment identification of the measurement and control equipment, and the switching time threshold of the measurement and control equipment in tracking the spacecraft twice; a first constraint on the number of spacecraft simultaneously tracked by the measurement and control equipment, wherein the first constraint includes the identification of the measurement and control equipment, and the maximum number of spacecraft simultaneously tracked by the measurement and control equipment; a second constraint on the number of spacecraft simultaneously uplinked by the measurement and control equipment, wherein the second constraint includes the identification of the measurement and control equipment, and the maximum number of spacecraft simultaneously uplinked by the measurement and control equipment; a third constraint on the number of spacecraft simultaneously downlinked by the measurement and control equipment, wherein the third constraint includes the identification of the measurement and control equipment, and the maximum number of spacecraft simultaneously downlinked by the measurement and control equipment; a fourth constraint on the number of links simultaneously uplinked by the measurement and control equipment, wherein the fourth constraint includes the identification of the measurement and control equipment, and the maximum number of links simultaneously uplinked by the measurement and control equipment.

[0047] The switching time constraint conditions of the above-mentioned measurement and control equipment, where the switching time constraint conditions include the equipment identification of the measurement and control equipment and the switching time threshold of the measurement and control equipment in two tracking of the spacecraft, require that in the two trackings corresponding to the measurement and control equipment, the time interval between the end time of the previous tracking and the start time of the next tracking must meet the switching time threshold, otherwise the measurement and control equipment will be difficult to execute.

[0048] Correspondingly, the number constraint condition one for the spacecraft that the measurement and control equipment can track simultaneously includes the identification of the measurement and control equipment and the maximum number of spacecraft that the measurement and control equipment can track simultaneously. That is, the number of spacecraft that the measurement and control equipment can track simultaneously shall not exceed the maximum number of the above-mentioned number constraint condition one.

[0049] The second quantity constraint condition for the number of spacecraft that can be simultaneously launched by the measurement and control equipment includes the identification of the measurement and control equipment and the maximum number of spacecraft that can be simultaneously launched by the measurement and control equipment. That is, the number of spacecraft that can be simultaneously launched by the measurement and control equipment shall not exceed the maximum number of the above-mentioned second quantity constraint condition.

[0050] The number of spacecraft that can simultaneously downlink the measurement and control equipment must not exceed the maximum number of the above-mentioned number constraint three.

[0051] The number of links of the measurement and control equipment that are simultaneously uplinked shall be limited to four, wherein the number of links of the measurement and control equipment that are simultaneously uplinked shall be limited to four, including the identification of the measurement and control equipment and the maximum number of links of the measurement and control equipment that are simultaneously uplinked. That is, the number of links of the measurement and control equipment that are simultaneously uplinked shall not exceed the maximum number of the above number of constraints four.

[0052] The above constraint conditions may also be other constraint conditions, which may be set according to specific detection requirements.

[0053] Optionally, determining the first measurement and control parameter of the measurement and control device, and the second measurement and control parameters corresponding to multiple spacecraft supported by the measurement and control device includes: obtaining a resource file in a first preset format of the measurement and control device based on the first device identifier of the measurement and control device, wherein the resource file includes the first device identifier and the first measurement and control parameter of the measurement and control device; and obtaining requirement files in a second preset format for multiple spacecraft based on the second device identifier of the spacecraft, wherein the requirement files include the second device identifier of the corresponding spacecraft, and the second measurement and control parameter.

[0054] The above file format can be XML format, which is convenient and quick to read. Figure 2As shown, the first device identifier may be a measurement and control device ID and a measurement and control device name. It may also include information such as a measurement and control device number. Figure 3 As shown, the second device identifier can be a spacecraft ID, a spacecraft name, etc. The formats of the resource file and the requirement file can be the same, both of which can be in the form of a file header + data area, the file header is used to store the first device identifier or the second device identifier, and the data area is used to store the first measurement and control parameters or the second measurement and control parameters.

[0055] Optionally, after testing the set of measurement and control items according to preset constraints, the first measurement and control parameters and the second measurement and control parameters, the method also includes: recording the test results one by one and generating a test report for subsequent query and use; marking illegal measurement and control items in the test results as illegal measurement and control items for subsequent query and use.

[0056] It should be noted that this embodiment also provides an optional implementation, which is described in detail below.

[0057] This embodiment provides a method for detecting conflicts in the allocation of multi-target spacecraft measurement and control resources, so as to effectively solve the technical problem of detecting conflicts in the allocation of multi-target spacecraft measurement and control resources. By using the method of the present invention, the results of the allocation of spacecraft measurement and control resources can be quickly and automatically detected. The present invention effectively solves the problem of conflict detection in the combined use of space-based and ground-based measurement and control resources by multiple spacecraft, and further improves the flexibility and convenience of the verification of the combined planning results of measurement and control resources of multiple spacecraft for complex aerospace measurement and control tasks.

[0058] A multi-target spacecraft measurement and control resource conflict detection method, the method comprising the following steps:

[0059] Step S11, determine the simultaneous uplink and downlink capabilities of each measurement and control device through the capability parameters of the measurement and control device. The capability parameters of the measurement and control device are used to describe the measurement and control support capabilities of a single measurement and control device, which is also the first measurement and control parameter mentioned above. The capability parameters of the measurement and control device are identified by an XML file including the following fields. The measurement and control device capability description file, which is also the resource file mentioned above, consists of two parts: "file header + data area". The corresponding model diagram is as follows: Figure 2 As shown, Figure 2 Schematic diagram of capability parameters of a measurement and control device according to an embodiment of the present invention.

[0060] Step S12, determining the simultaneous uplink and downlink capabilities of each spacecraft through the spacecraft capability parameters. The spacecraft capability parameters are used to describe the simultaneous uplink and downlink support capabilities of a single spacecraft. The spacecraft capability parameters include: Figure 3 The XML file identifier of the fields shown in the figure. The spacecraft uplink and downlink measurement and control capability description file, that is, the above-mentioned requirement file, consists of two parts: "file header + data area". The corresponding model diagram is as follows Figure 3 As shown, Figure 3 is a schematic diagram of capability parameters of a spacecraft according to an embodiment of the present invention.

[0061] Step S13, determine the description set of each spacecraft measurement and control resource allocation project, that is, the measurement and control project set. Specifically, extract each spacecraft measurement and control resource allocation project from various measurement and control resource allocation results to obtain the measurement and control resource allocation project set. A single spacecraft measurement and control resource allocation project includes the following fields:

[0062] (1) Assign an ID, a unique identifier;

[0063] (2) Device ID, unique identifier;

[0064] (3) Spacecraft ID, unique identification;

[0065] (3) Equipment tracking start time;

[0066] (4) Equipment tracking end time;

[0067] (5) The time when the device starts receiving downlink data;

[0068] (6) The time when the device ends downlink reception;

[0069] (7) Downlink receiving frequency of the device;

[0070] (8) The time when the device starts uplinking;

[0071] (9) The time when the device ends uplinking;

[0072] (10) Equipment uplink frequency.

[0073] Step S104, check according to the constraint conditions. Determine a set of one or more constraint conditions arranged in order to form a detection rule stack. The common content of each constraint condition description includes constraint ID, constraint type, and constraint description. The measurement, control and tracking constraint detection rules may include the following types:

[0074] (1) Equipment switching duration constraint type;

[0075] (2) The threshold detection constraint type for the number of targets that can be tracked simultaneously by the same device;

[0076] (3) The same device simultaneously receives the target number of downlinks. The detection constraint type;

[0077] (4) The same device supports the target number of simultaneous uplinks.

[0078] (5) The type of constraint detection for the number of simultaneous uplinks from the same spacecraft.

[0079] The constraint values ​​and constraint value detection rules corresponding to each of the above constraint types are as follows:

[0080] (1) Device switching duration constraint type: Enter the device ID and switching duration.

[0081] Detection rule: In the two trackings corresponding to this device, the difference between the previous end time and the next start time cannot be less than this value.

[0082] (2) Threshold constraint type for the number of targets tracked simultaneously by the same device: Enter a positive integer.

[0083] Detection rules: The maximum number of targets that the device can track at the same time cannot exceed this value.

[0084] (3) The threshold detection constraint type for the number of simultaneous downlink reception targets of the same device: Enter a non-negative integer.

[0085] Detection rule: The maximum number of downlink receiving targets of the device at the same time cannot be higher than this value.

[0086] (4) Threshold detection constraint type for the number of simultaneous uplink targets of the same device: Enter a non-negative integer.

[0087] Detection rule: The maximum number of uplink targets of the device at the same time cannot be higher than this value.

[0088] (5) Threshold detection constraint type for the number of simultaneous uplinks from the same spacecraft: Enter a non-negative integer.

[0089] Detection rule: The maximum number of uplinks of the spacecraft at the same time cannot be higher than this value.

[0090] The capability parameters of a single measurement and control device may include device ID, downlink measurement and control point frequency support capability description, uplink measurement and control point frequency support capability description, supported target data and elevation angle constraints, etc.

[0091] A single spacecraft tracking and control resource allocation item description set may include allocation ID, equipment ID, spacecraft ID, tracking start and end time, downlink reception start and end time, and uplink start and end time.

[0092] The constraint condition set may include one or more constraint sets arranged in order. Each constraint description includes constraint ID, constraint type, and constraint description.

[0093] The above-mentioned multiple constraints may also include: device switching time constraint, target number threshold constraint for simultaneous tracking support by the same device, target number threshold detection for simultaneous downlink reception by the same device, target number threshold detection for simultaneous uplink reception by the same device, and target number threshold detection for simultaneous uplink reception by the same spacecraft.

[0094] Figure 4 is a schematic diagram of a conflict detection device for aerospace tracking and control resource allocation according to an embodiment of the present invention. Figure 4 As shown, it includes: a determination module 42, an acquisition module 44 and a detection module 46. The device is described in detail below.

[0095] A determination module 42 is used to determine a first measurement and control parameter of a measurement and control device, and a second measurement and control parameter corresponding to each of a plurality of spacecraft supported by the measurement and control device, wherein the measurement and control device is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; an acquisition module 44 is connected to the above-mentioned determination module 42, and is used to acquire a plurality of measurement and control items of a plurality of spacecraft to obtain a set of measurement and control items; a detection module 46 is connected to the above-mentioned acquisition module 44, and is used to detect the set of measurement and control items according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, wherein the constraints include a plurality of constraints on the measurement and control device, the spacecraft, or the data transmission between the measurement and control device and the spacecraft.

[0096] Through the above-mentioned device, a first measurement and control parameter of the measurement and control equipment and a second measurement and control parameter corresponding to a plurality of spacecraft supported by the measurement and control equipment are determined, wherein the measurement and control equipment is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control equipment, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; a plurality of measurement and control items of the plurality of spacecraft are obtained to obtain a measurement and control item set; the measurement and control item set is detected according to preset constraints, the first measurement and control parameter and the second measurement and control parameter, wherein the constraints include a plurality of constraints on the measurement and control equipment, the spacecraft or the data transmission between the measurement and control equipment and the spacecraft, and the measurement and control item set is detected by the preset constraints, the first measurement and control parameter and the second measurement and control parameter, so as to achieve the purpose of setting the measurement and control item set by setting the constraints according to the requirements, thereby achieving the technical effect of improving the flexibility of the measurement and control item detection and detecting the measurement and control item set according to the requirements, thereby solving the technical problem that the measurement and control resources of the plurality of spacecrafts in parallel in the related technology are prone to conflict, and the current method of only detecting the conflict of the support capability of the number of uplink targets is poor in flexibility and difficult to meet the requirements.

[0097] According to another aspect of an embodiment of the present invention, a processor is provided, and the processor is used to run a program, wherein when the program is run, any one of the above-mentioned conflict detection methods for allocation of aerospace tracking and control resources is executed.

[0098] According to another aspect of an embodiment of the present invention, a computer storage medium is provided, the computer storage medium including a stored program, wherein when the program is running, the device where the computer storage medium is located is controlled to execute any one of the above-mentioned conflict detection methods for the allocation of aerospace tracking and control resources.

[0099] The serial numbers of the above embodiments of the present invention are only for description and do not represent the advantages or disadvantages of the embodiments.

[0100] In the above embodiments of the present invention, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0101] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. Among them, the device embodiments described above are only schematic. For example, the division of the units can be a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, which can be electrical or other forms.

[0102] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple units. Some or all of the units may be selected according to actual needs to achieve the purpose of the present embodiment.

[0103] In addition, each functional unit in each embodiment of the present invention may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0104] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), mobile hard disk, magnetic disk or optical disk and other media that can store program codes.

[0105] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A conflict detection method for aerospace measurement and control resource allocation, It is characterized in that include: Determine a first measurement and control parameter of a measurement and control device, and second measurement and control parameters respectively corresponding to a plurality of spacecraft supported by the measurement and control device, wherein the measurement and control device is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; Acquire multiple measurement and control projects of the multiple spacecraft to obtain a measurement and control project set; According to preset constraints, the first measurement and control parameter and the second measurement and control parameter, the measurement and control item set is detected, wherein the constraints include multiple constraints on the measurement and control equipment, the spacecraft, or data transmission between the measurement and control equipment and the spacecraft; According to the preset constraint conditions, the first measurement and control parameter and the second measurement and control parameter, before detecting the measurement and control item set, it also includes: obtaining a plurality of preset constraint conditions, wherein each of the constraint conditions at least includes: a constraint object and a constraint behavior; according to the sequence in which the constraint objects targeted by the plurality of constraint conditions execute corresponding constraint behaviors in the measurement and control items, storing the plurality of constraint conditions in a target rule stack; According to the preset constraints, the first measurement and control parameters and the second measurement and control parameters, the detection of the measurement and control project set includes: selecting the first measurement and control project in the measurement and control project set according to the preset order; according to the multiple constraints in the target rule stack, in the order of priority, respectively detecting whether the constraint behavior of the constraint object of the measurement and control project satisfies the corresponding constraint; when the measurement and control project passes the detection of all the constraints in the target rule stack, detecting the execution parameters of the measurement and control equipment of the measurement and control project according to the first measurement and control parameters, and detecting the execution parameters of the spacecraft of the measurement and control project according to the second measurement and control parameters; when the measurement and control project passes the first measurement and control parameters and the second measurement and control parameters, determining that the measurement and control project passes the detection; selecting the next measurement and control project from the measurement and control project set according to the preset order for detection until all the measurement and control projects in the measurement and control project set have completed the detection.

2. The method according to claim 1, It is characterized in that Determining a first measurement and control parameter of a measurement and control device and second measurement and control parameters corresponding to a plurality of spacecraft supported by the measurement and control device respectively comprises: According to the first device identification of the measurement and control device, obtaining a resource file of the measurement and control device in a first preset format, wherein the resource file includes the first device identification of the measurement and control device and the first measurement and control parameter; According to the second device identification of the spacecraft, the requirement files of the second preset format of the multiple spacecraft are respectively obtained, wherein the requirement files include the second device identification of the corresponding spacecraft and the second measurement and control parameters.

3. The method according to claim 2, It is characterized in that The first measurement and control parameter includes at least one of the following: a downlink measurement and control point frequency support capability parameter, a number of spacecraft supported simultaneously in the downlink, an uplink measurement and control point frequency support capability parameter, a number of spacecraft supported simultaneously in the uplink, and an uplink elevation angle constraint parameter; The second measurement and control parameter includes at least one of the following: downlink measurement and control point frequency support capability parameter, the number of simultaneously supported downlink point frequencies, uplink measurement and control point frequency support capability parameter, the number of measurement and control devices simultaneously supported uplink, and ground-based measurement and control support capability parameter.

4. The method according to claim 2, It is characterized in that The measurement and control project corresponds to the identification of the equipment or data involved in the project, and the measurement and control project parameters between the measurement and control equipment and the spacecraft corresponding to the measurement and control project; The identification includes at least one of the following: an allocation identification, a first device identification, and a second device identification; The measurement and control project parameters include at least one of the following: The measurement and control equipment tracks the start time and the end time of the corresponding spacecraft in the measurement and control project; The uplink start time, uplink end time, downlink start time and downlink end time between the measurement and control equipment and the corresponding spacecraft; The uplink point frequency and the downlink point frequency between the measurement and control equipment and the spacecraft corresponding to the measurement and control equipment.

5. The method according to claim 1, It is characterized in that The multiple constraints include: The switching time constraint condition of the measurement and control device, wherein the switching time constraint condition includes a device identification of the measurement and control device and a switching time threshold of the measurement and control device in two trackings of the spacecraft; A first constraint condition on the number of spacecraft that can be simultaneously tracked by the measurement and control device, wherein the first constraint condition includes an identifier of the measurement and control device and a maximum number of spacecraft that can be simultaneously tracked by the measurement and control device; A second constraint condition on the number of spacecraft that can be launched simultaneously by the measurement and control equipment, wherein the second constraint condition on the number includes an identifier of the measurement and control equipment and a maximum number of spacecraft that can be launched simultaneously by the measurement and control equipment; A third constraint condition on the number of spacecraft that can be simultaneously downlinked by the measurement and control equipment, wherein the third constraint condition on the number includes an identifier of the measurement and control equipment and a maximum number of spacecraft that can be simultaneously downlinked by the measurement and control equipment; A fourth constraint condition on the number of simultaneously uplink links of the measurement and control device, wherein the fourth constraint condition includes an identifier of the measurement and control device and a maximum number of simultaneously uplink links of the measurement and control device.

6. The method according to claim 5, It is characterized in that After detecting the measurement and control item set according to the preset constraint condition, the first measurement and control parameter and the second measurement and control parameter, the method further includes: Record the test results one by one and generate a test report; Mark illegal measurement and control items in the detection results as illegal measurement and control items.

7. A conflict detection device for aerospace measurement and control resource allocation, It is characterized in that include: A determination module, used to determine a first measurement and control parameter of a measurement and control device, and second measurement and control parameters respectively corresponding to a plurality of spacecraft supported by the measurement and control device, wherein the measurement and control device is used to provide measurement and control resources for the plurality of spacecraft supported, the first measurement and control parameter is used to characterize the measurement and control capability of the measurement and control device, and the second measurement and control parameter is used to characterize the measurement and control capability of the spacecraft; An acquisition module, used for acquiring a plurality of measurement and control items of the plurality of spacecraft to obtain a measurement and control item set; a detection module, configured to detect the measurement and control item set according to preset constraints, the first measurement and control parameter, and the second measurement and control parameter, wherein the constraints include multiple constraints on the measurement and control equipment, the spacecraft, or data transmission between the measurement and control equipment and the spacecraft; The conflict detection device for aerospace measurement and control resource allocation is also used for: obtaining a plurality of preset constraint conditions before detecting the measurement and control project set according to the preset constraint conditions, the first measurement and control parameter and the second measurement and control parameter, wherein each of the constraint conditions at least includes: a constraint object and a constraint behavior; storing the plurality of constraint conditions in a target rule stack according to the order in which the constraint objects targeted by the plurality of constraint conditions execute corresponding constraint behaviors in the measurement and control project; The detection module includes: a project selection submodule, which is used to select the first measurement and control project in the measurement and control project set according to a preset order; a condition detection submodule, which is used to detect whether the constraint behavior of the constraint object of the measurement and control project satisfies the corresponding constraint conditions according to the plurality of constraint conditions in the target rule stack in the sequence; a parameter detection submodule, which is used to detect the execution parameters of the measurement and control equipment of the measurement and control project according to the first measurement and control parameters, and to detect the execution parameters of the spacecraft of the measurement and control project according to the second measurement and control parameters when the measurement and control project passes the detection of all the constraint conditions in the target rule stack; a project pass detection submodule, which is used to determine that the measurement and control project passes the detection when the measurement and control project passes the first measurement and control parameters and the second measurement and control parameters; and a project sequence detection submodule, which is used to select the next measurement and control project from the measurement and control project set according to the preset order for detection until all the measurement and control projects in the measurement and control project set have completed the detection.

8. A processor, It is characterized in that The processor is used to run a program, wherein the program, when running, executes the conflict detection method for aerospace measurement and control resource allocation described in any one of claims 1 to 6.

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