KR20170121833A - Flight Dynamics Subsystem Of Satellite Control System - Google Patents

Abstract

Below, a flight dynamics subsystem inside a satellite control system is disclosed. According to an embodiment, the flight dynamics subsystem comprises: first components having unique performance in control of a satellite; and a processor preforming functions of flight dynamics by using at least a portion of second components reused for controlling another satellite.

Description

[0001] Flight Dynamics Subsystem of Satellite Control System [

The following embodiment relates to a flight dynamics subsystem in a satellite control system and its operation.

The geostationary control system generates a real-time operating subsystem consisting of a telemetry system that sends remote commands to the satellites in real time and receives information about the operational state or operation of the satellites, parameters for supporting satellite operations and mission performance, (Telemetry Tracking and Command System) subsystem, which is a hardware related system, such as a flight dynamics sub-system that calculates the position information and the amount of fuel used, and an antenna / modem BB that transmits and receives data to the satellite.

Among these control systems, the flight dynamics subsystem can perform orbit determination in a single ground station using azimuth, elevation angle, and distance measurement data. When two or more ground stations are used, distance measurement data and each tracking data are used to determine the orbit Can be determined. The trajectory prediction (orbital propagation) is performed using the determined orbit, and the parameters required for the satellite operation are calculated by performing functions such as event prediction, position adjustment, and position movement as a result of the orbit prediction. It should also have the ability to calculate the amount of fuel to estimate the lifetime of the remaining satellites and to update the satellite and ground station information associated with the satellite bus body.

Each function can be separated into modules and these can be configured as components to replace the components required by other satellites, and those defined as libraries can be recalled as needed.

There have been studies to develop a componentized algorithm for each function of flight mechanics. The satellite control system developed as a flight dynamics sub-system by connecting components to each other so that the functions can be used not only in geostationary orbitals but also in other low orbit satellites, It can operate on satellites.

In the case of the flight dynamics subsystem, most of the tests whether the performance results according to the user requirements are satisfied. For satisfying the performance, most of the functions must be satisfied, so that it can be verified as a result of the performance test. It is also an important issue to verify and manage the test results easily during the development process.

According to an embodiment of the present invention, a satellite control system in which each function of the flight dynamics subsystem is subdivided and modularized on a component basis is provided. Each of the subdivided modules or functions can be componentized to be applicable to other satellites.

Also, we want to develop a system that can set up test items and quality indicators (Tolerance) for testing, and componentize and manage tools to perform tests using them.

CLAIMS What is claimed is: 1. A flight dynamics subsystem in a satellite control system for controlling a satellite, comprising: at least one first component comprising a unique algorithm for controlling the satellite; And a processor for performing a plurality of functions for flight ephemeris of the satellite using at least one second component that is reusable in the control of another satellite.

In one aspect, the at least one first component may include at least one of a thruster modeling component, a location-and-restoration reconstruction component, a location relocation and orbital reconstruction component, and a fuel computation module component.

In yet another aspect, the at least one first component may be redesigned upon the control of the other satellite.

In another aspect, the at least one second component is selected from the group consisting of a dynamic model component, a filter model component, a coordinate transform component, a time transform component, a measurement process component, an ephemeris component, an integrator component, Planning component, co-location strategy S / C combination analysis component, sensor component, and interference model component.

According to another aspect of the present invention, the functions of the flight mechanics include a function of determining the orbit of the satellite, a function of predicting orbit of the satellite, a function of adjusting the position of the satellite, a function of juxtaposing the satellite, A system management function, and an onboard update function of the satellite.

In another aspect, the processor is capable of data communication through an interface between the at least one first component and the at least one second component.

In another aspect, the processor may configure a GUI that provides an interface with a user to execute the function of the flight dynamics using an API.

According to another aspect of the present invention, there is provided a method of analyzing the functions of the flight mechanics by receiving function-specific error ranges and reference data of the flight mechanics, performing functions of the flight mechanics, The verification device may further comprise a verification device.

In another aspect, the processor comprises: a third component redesigned based on a unique algorithm for the control of a second satellite distinct from the satellite; And to perform a plurality of functions for the flight dynamics of the second satellite using the at least one second component.

According to the embodiment, in the case of the flight dynamics subsystem which is easy to reuse and relocate among the geostationary satellite control system, each function is implemented for each component and the interface to connect them is defined, so that the time and cost Can be saved.

1 is a block diagram of a flight dynamics subsystem of geostationary-satellite in one embodiment.
FIG. 2 is a block diagram illustrating the configuration of components of the flight dynamics subsystem, in one embodiment.
3 is a block diagram for explaining a method of generalizing the format of observation data for determining the orbit of a satellite in one embodiment.
4 is an example of a GUI provided in the flight dynamics subsystem, in one embodiment.
5 is a block diagram for explaining the operation of the verification tool (device) in one embodiment.
6 is a diagram illustrating a scenario for verifying a flight dynamics subsystem using a verification device, in one embodiment.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

Various modifications may be made to the embodiments described below. It is to be understood that the embodiments described below are not intended to limit the embodiments, but include all modifications, equivalents, and alternatives to them.

The terms used in the examples are used only to illustrate specific embodiments and are not intended to limit the embodiments. The singular expressions include plural expressions unless the context clearly dictates otherwise. In this specification, the terms "comprises" or "having" and the like refer to the presence of stated features, integers, steps, operations, elements, components, or combinations thereof, But do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or combinations thereof.

Unless defined otherwise, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this embodiment belongs. Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the contextual meaning of the related art and are to be interpreted as either ideal or overly formal in the sense of the present application Do not.

In the following description of the present invention with reference to the accompanying drawings, the same components are denoted by the same reference numerals regardless of the reference numerals, and redundant explanations thereof will be omitted. In the following description of the embodiments, a detailed description of related arts will be omitted if it is determined that the gist of the embodiments may be unnecessarily blurred.

In the embodiment, components for each module included in the flight dynamics subsystem of the satellite control system or functions that can be reused can be made into components and reused and relocated, and quality indices and test tools for the flight dynamics sub system are provided .

1 is a block diagram of a flight dynamics subsystem of geostationary-satellite in one embodiment.

The flight dynamics subsystem 100 according to an embodiment may include components 110 and an API 120. The components 110 may include at least one first component including a unique algorithm for satellite control and at least one second component including a reusable algorithm for control of another satellite.

The flight dynamics subsystem 100 may utilize the first and second components of the components 110 through the processor to perform the functions of flight dynamics in a satellite control. For example, one function may be performed through one component or a function may be performed through a plurality of components.

The functions performed in the flight dynamics subsystem 100 include satellite orbit determination, satellite orbital prediction, satellite position adjustment, satellite positioning, satellite juxtaposition, satellite fuel consumption estimation, satellite system Management, and satellite on-board update functionality.

In an embodiment, it may be comprised of modules that play an important role in the flight dynamics subsystem 100 for performing the respective functions of the components 110, for example, the first component may be a thruster modeling component, Wherein the first component comprises at least one of a position-and-restoration reconstruction component, a position relocation and an orbital restoration reconstruction component, and a fuel calculation module component, the second component comprising at least one of a kinematic model component, a filter model component, At least one of a component, an ephemeris component, an integrator component, a location maintenance component, a location adjustment and orbital movement planning component, a co-location strategy S / C combination analysis component, a solar and eclipse prediction component, a sensor blinding prediction component, . ≪ / RTI >

An embodiment in which the components are used will be described later in detail with reference to FIG.

 Each function can create a GUI corresponding to each function in the API 120 and communicate with the user through the interface.

Among the functions of the flight mechanics 110, the components given by the algorithm may be able to interface with the user through an application tool such as a GUI. Each component should be able to interface internally with input / output files. The GUI for the user's convenience can be linked with the algorithm developed as a component of the flight mechanics and easily changed to the GUI desired by the user.

The basic components of the respective algorithms among the components 110 may have an interface capable of inputting and outputting data to and from one another with respect to at least one function and each interface may be provided so as to match the file format. And may include compatible converters. The API 120 includes a main window (window) and is capable of communicating with each other about the capabilities of each component within the components 110.

In an embodiment of the invention, a verification device 130 may be provided for verifying operation of the flight dynamics subsystem 100. The verification device 130 according to the embodiment may be provided as a tool installed in the flight dynamics subsystem 100 or may be provided as a separate device.

The verification device 130 may measure the performance of each component used for all functions performed in the flight dynamics subsystem 100 for satellite control. The verification device 130 may store a value that is a performance criterion for each function in advance or may be input through the user. For example, when receiving a value as a performance criterion, a GUI provided through the API 120 may be used by the user. Performance criteria may be set for each component that operates on each function.

FIG. 2 is a block diagram illustrating the configuration of components of the flight dynamics subsystem, in one embodiment.

In an embodiment, a granular configuration is shown for components 110 of a Flight Dynamic Subsystem (FDS) 100. Each component is componentized for the capabilities used for different satellites or navigation by function, and can provide a reusable and relocatable configuration.

The first components 111 are unique algorithms that rely on a satellite bus body and include capabilities that require a new algorithm redesign for each other satellite control system.

For example, the first component may include at least one of a thruster modeling component, a location-and-restoration reconstruction component, a location relocation and orbital reconstruction reconfiguration component, and a fuel computation module component.

The second components 112 may include reusable capabilities for performing various functions on the satellite control.

For example, the second component may be a dynamic model component, a filter model component, a coordinate transform component, a time transform component, a measurement process component, an ephemeris component, an integrator component, a position maintenance component, a position adjustment and orbital movement planning component, A strategy S / C combination analysis component, a solar and eclipse prediction component, a sensor blinding prediction component, and an interference component.

The components used to perform each function will be described. As described above, the functions of flight mechanics include satellite orbit determination, satellite orbit prediction, satellite position adjustment, satellite position shift, satellite juxtaposition operation, satellite fuel consumption estimation, satellite system management, satellite A bus-dependent Onboard update function, and the like.

Orbit determination and orbital prediction are similar concepts, but by subdividing the performance for these functions into components, it is possible to use not only other satellites but also geostationary / medium orbit / low orbit satellites, or related guidance and navigation Reuse and relocation may be possible.

In the embodiment, in order to perform the function of determining the orbit, a filter for processing the observation data according to the mission characteristics or the user's demand and calculating an optimized value of the approximate calculated value with respect to the observation data value and the position of the satellite ) Component, for example, a batch filter, a Kalmann filter, an extended Kalman filter, and a particle filter can be applied. The filter can be applied to find the orbital elements corresponding to the initial estimated epoch. Here, the process of the observation data is mainly used for each tracking data (azimuth angle, elevation angle) and ranging data in the case of geostationary satellite, and data about the bias and noise for the corresponding values Editing may be performed. Then, using kinetic components, we can calculate the satellite orbital elements by calculating the position of the satellite at each time. In the case of geostationary satellites, the interference due to the Earth's gravitational field (perturbation), the solar perturbation, / Using a dynamical model component consisting of perturbations by other planets, and integrating it with respect to time using an integrator component.

In one embodiment, the trajectory prediction (orbital propagation) function applies an orbit component to the initial component of the trajectory determined by the trajectory determination to the kinetic component, and displays the result of the trajectory prediction with the integrated value at each time in the integrator component .

In one embodiment, the function of the position maintenance adjustment may be converted to an average orbital element using the predicted orbit, and the position maintenance adjustment plan may be calculated for the east-west direction and the north-south direction using the position maintaining component. Here, it can be applied to each of the algorithms for the east-west direction and the north-south direction, and in the case of the north-south direction, the maneuver time can be calculated differently depending on the position of the thruster component. With respect to the orbital modification plan of the position maintenance adjustment component, reconstruction is performed by the thruster information and detailed related model (thruster modeling), which can utilize the satellite manufacturer's algorithm as a bus dependency function of the satellite.

In one embodiment, the function of the position movement is to move to a circular orbit in a circular orbit as a function of the orbital motion planning component with respect to geosynchronous satellites, and if there are other satellites in motion, .

In one embodiment, the function of the fuel amount calculation may correspond to a bus body dependency function for each thruster calculated on the ground, using information on the fuel amount used in the satellite coming off the on-board and the thruster component .

In one embodiment, the system management functions may correspond to functions of each directory and folder of the flight dynamics subsystem 100, login and logout, database management, and interface management.

In one embodiment, the satellite juxtaposition operating function includes scenarios optimized for cases where several geostationary satellites are within the same longitude, and is intended to operate within a given mission interval longitude and latitude of the satellite. The satellite juxtaposition function may include a function of generating a warning message or an alarm when the minimum distance between two satellites is close to each other by calculating the positions of two or more satellites so that they do not collide with each other in the event of a risk of collision between the satellites have.

In the embodiment, in order to generalize (standardize) the observation data format for orbit determination, in most cases, the satellites are controlled by the satellite producer during the Launch and Early Orbit Phase (LEOP) or IOT In this case, since the developer of the control system and the satellite producer are different from each other in performing the orbit determination at this time, the data formats on the system of the developer and the manufacturer are not compatible with each other. Thus, the format can be generalized as shown in FIG.

3 is a block diagram for explaining a method of generalizing the format of observation data for determining the orbit of a satellite in one embodiment.

In an embodiment, a script (Translator) 300 may be used to change the format of another site, system 200, to the format of the flight dynamics subsystem 100, or to change the format of the flight dynamics subsystem 100 to another To the format of the system 200. The method of FIG.

It is possible to divide the header part of the translator 300 into a part for generating a data value and an epoch part for generating a data value. In the header portion of the translator 300, the date and / or the date of creation of the data file are usually input, but often occur. Therefore, the conditional statement can be processed in the translator 300.

You can check if the Azimuth (azimuth) exists for the data file and see if Azimuth is radian or degree. Elevation (elevation) can also be checked. In the case of a range (range), it is checked whether it is the same as R / Range, whether the unit is km or m, and others are defined in the translator 300 for the first type so that the format can be changed. The translator 300 can recognize and translate by type or value.

4 is an example of a GUI provided in the flight dynamics subsystem, in one embodiment.

In the embodiment, a GUI for interfacing the components 110 with the user may be created for the functions of the flight dynamics subsystem described with reference to FIG. 1 and FIG. 2 to implement an interface with the user.

The aviation dynamics subsystem can generate a GUI tool related to flight mechanics by using the API 120 to create a GUI as desired by the user.

The elements mainly composed of the GUI window in the flight dynamics subsystem include items for selecting epoch and orbit element files, buttons for processing results, and other main input parameters, There are algorithm options to choose from for motion adjustments, and orbit determination and event ground station information to choose from.

The main functions of the flight dynamics subsystem can be displayed as a GUI in a library. For example, a GUI can be created by clicking and inputting a mouse or a keyboard as desired by a user, and a data file and / DB) You can connect to each other through the GUI to input files.

5 is a block diagram for explaining the operation of the verification tool (device) in one embodiment.

The verification device 130 for the flight dynamics subsystem verifies the operation of the functions for the functions performed by the components 110 shown in FIG. 1, except for the system management, the database management, and the modeling of the thruster .

For each function, reference data can be generated in advance or input via the user, and a database suitable for the environment can be set for verification. You can get input about tolerance ranges that must satisfy each function that is a quality indicator.

To generate the reference data so that verification can be performed on the flight dynamics subsystem, the database and parameters for verification can be input and each function of the flight dynamics subsystem can be performed for actual verification. Alternatively, it is possible to generate reference data corresponding to each function by using an application that has already been verified and performs highly reliable flight dynamics.

In the verification apparatus 130 for verifying the components, in the case of the orbit determination, it is possible to calculate whether the orbit determination tolerance is within the range by covariance. In the case of the trajectory prediction, it is possible to verify how much error exists with reference trajectory value, and in the event prediction function, it is possible to check whether the error of the event occurrence time is within the tolerance range.

For location maintenance, you can check whether it is within a given mission longitude interval, perform a plot or trend analysis, and compare it to other reliable software results. For the locomotion function, you can verify that you have entered the target longitude correctly and compare the orbit shift time and speed increment with other reliable software results. Fuel quantity calculation and onboard update functions can be verified by comparing the results of the test data provided by the satellite manufacturer of the bus body.

By comparing the performance results for each function, the results for success and failure can be output. Here, errors for each function should be defined for verification, and it can be defined as a script or a text file format so that it can be input on a GUI or read a file. Thereafter, the verification result can be managed by the user.

6 is a diagram illustrating a scenario for verifying a flight dynamics subsystem using a verification device, in one embodiment. In an embodiment, a highly reliable flight mechanics application 300 that is in use to generate reference data may be used.

Although the flight mechanics application 300 is not componentized and used in correspondence with the flight mechanics function, in an embodiment, the verification device may be configured to perform internal operations of the flight mechanics application 300 by function, e.g., A first function, a second function, a third function, and the like.

The verification device according to one embodiment may match a plurality of components constituting the flight dynamics subsystem 100 to each of the functions of the flight dynamics application 300 to verify the flight dynamics subsystem 100 on a component by component basis .

For example, the components of the flight dynamics subsystem 100 may be classified into a first group for performing a first function, for example, a component A, a component B, and a component C, The component E may be classified into a second group for performing a second function, the component F may be classified into a third group for performing a third function, and an output obtained by performing a function in each group corresponding to the input Can be obtained. Each group of flight dynamics subsystem 100 may correspond to each function of the flight dynamics application 300.

In the illustrated embodiment, the first, second, and third functions are sequentially performed. However, the functions may be performed in parallel, and when the component is classified by function for the flight dynamics subsystem 100, One component may be classified to be included in two or more groups. For example, although not shown in the drawing, the component E belongs to the second group and can also belong to the third group.

In an embodiment, the flight dynamics subsystem 100 may extract outputs for each function or group that corresponds to the input. When the flight mechanics application 300 is operated, one output may be generated in response to the input. However, the operation corresponding to each function may be distinguished and extracted according to the function of the application.

The verification device 130 can use the extracted output for each function of the flight kinematics application 300 as reference data. For example, the verification device 130 can output the output of each function of the flight kinematics application 300, Verification of the system can be performed by comparing the outputs for each function of the flight dynamics subsystem 100. [

The embodiments described above may be implemented in hardware components, software components, and / or a combination of hardware components and software components. For example, the devices, methods, and components described in the embodiments may be implemented within a computer system, such as, for example, a processor, a controller, an arithmetic logic unit (ALU), a digital signal processor, such as an array, a programmable logic unit (PLU), a microprocessor, or any other device capable of executing and responding to instructions. The processing device may execute an operating system (OS) and one or more software applications running on the operating system. The processing device may also access, store, manipulate, process, and generate data in response to execution of the software. For ease of understanding, the processing apparatus may be described as being used singly, but those skilled in the art will recognize that the processing apparatus may have a plurality of processing elements and / As shown in FIG. For example, the processing unit may comprise a plurality of processors or one processor and one controller. Other processing configurations are also possible, such as a parallel processor.

The software may include a computer program, code, instructions, or a combination of one or more of the foregoing, and may be configured to configure the processing device to operate as desired or to process it collectively or collectively Device can be commanded. The software and / or data may be in the form of any type of machine, component, physical device, virtual equipment, computer storage media, or device , Or may be permanently or temporarily embodied in a transmitted signal wave. The software may be distributed over a networked computer system and stored or executed in a distributed manner. The software and data may be stored on one or more computer readable recording media.

The method according to an embodiment may be implemented in the form of a program command that can be executed through various computer means and recorded in a computer-readable medium. The computer-readable medium may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions to be recorded on the medium may be those specially designed and configured for the embodiments or may be available to those skilled in the art of computer software. Examples of computer-readable media include magnetic media such as hard disks, floppy disks and magnetic tape; optical media such as CD-ROMs and DVDs; magnetic media such as floppy disks; Magneto-optical media, and hardware devices specifically configured to store and execute program instructions such as ROM, RAM, flash memory, and the like. Examples of program instructions include machine language code such as those produced by a compiler, as well as high-level language code that can be executed by a computer using an interpreter or the like. The hardware devices described above may be configured to operate as one or more software modules to perform the operations of the embodiments, and vice versa.

Although the preferred embodiments of the present invention have been disclosed for illustrative purposes, those skilled in the art will appreciate that various modifications, additions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. For example, it is to be understood that the techniques described may be performed in a different order than the described methods, and / or that components of the described systems, structures, devices, circuits, Lt; / RTI > or equivalents, even if it is replaced or replaced. Therefore, other implementations, other embodiments, and equivalents to the claims are also within the scope of the following claims.

Claims (10)

CLAIMS 1. A flight dynamics subsystem in a satellite control system for controlling satellites,
At least one first component comprising a unique algorithm for controlling said satellite; And
At least one second component reusable for control of another satellite
A processor for performing a plurality of functions for the flight dynamics of the satellite,
/ RTI >
Flight dynamics subsystem.
The method according to claim 1,
The processor
Wherein the at least one first component and the at least one second component are grouped into groups for performing the separated functions based on the distinguished functions, And performing verification of each group component based on functional unit outputs of the verification flight mechanics application and group outputs of the flight dynamics subsystem,
Flight dynamics subsystem.
The method according to claim 1,
Wherein the at least one first component comprises:
A thruster modeling component, a location-and-restoration reconstruction component, a location relocation and orbital restoration reconstruction component, and a fuel calculation module component.
Flight dynamics subsystem.
The method according to claim 1,
Wherein the at least one first component comprises:
When the other satellite is controlled,
Flight dynamics subsystem.
The method according to claim 1,
Wherein the at least one second component comprises:
C / C coupling analysis component, coordinate transformation component, coordinate transformation component, time conversion component, measurement data process component, ephemeris component, integrator component, position maintenance component, position adjustment and orbital movement planning component, And at least one of a solar and eclipse planning component, a sensor blinding prediction component, and an interference model component.
Flight dynamics subsystem.
The method according to claim 1,
The functions of the flight mechanics,
A satellite tracking function, a satellite tracking function, a satellite tracking function, a satellite fuel tracking function, a system management function, an onboard update of the satellite, ≪ / RTI >
Flight dynamics subsystem.
The method according to claim 1,
The processor comprising:
Data communication via an interface between the at least one first component and the at least one second component
Flight dynamics subsystem.
The method according to claim 1,
The processor comprising:
A GUI for providing an interface with a user to execute the function of the flight dynamics using an API,
Flight dynamics subsystem.
The method according to claim 1,
A verification unit that receives the function-specific error range and reference data of the flight mechanics, performs the function of the flight mechanics, and verifies the functions of the flight mechanics using the comparison result with the error range and reference data
≪ / RTI >
Flight dynamics subsystem.
The method according to claim 1,
The processor
A third component redesigned based on a unique algorithm for the control of a second satellite distinct from the satellite; And
The at least one second component
And a plurality of functions for the flight dynamics of the second satellite are performed using the second satellite,
Flight dynamics subsystem.

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