Method and system for controlling satellite design and analysis tool in consideration of requirement determined by mission purpose and expected profit

Abstract

In order to solve the problem examined above, a satellite design and analysis method according to the present invention comprises the steps of: inputting a mission purpose for a satellite; specifying a design variable corresponding to the mission purpose; calculating a plurality of engineering characteristics for the satellite on the basis of the design variable; selecting at least one engineering characteristic related to a requirement among the plurality of engineering characteristics; calculating a suitability index of the selected at least one engineering characteristic with respect to the requirement; and outputting the suitability index to evaluate the design variable.

Description

Control method and system for satellite design and analysis tools considering requirements according to mission purpose and expected return

[0001] The present invention relates to a satellite design and analysis method and system, and more particularly, to a control method of a satellite design and analysis method tool considering requirements according to mission objectives and expected profits.

[0002] Microsatellites are satellites that can be produced in large numbers at low cost in a short period of time through the active use of commercial products. They have the advantage of easy development accessibility because they actively utilize commercial products.

[0003] Moreover, due to their low development costs, microsatellites can be utilized for challenging missions that were previously difficult to accomplish. In this regard, because challenging missions often lack the benefit of reference to previous mission results, decisions made in the early design stages significantly impact the overall mission development efficiency and costs.

[0004] Meanwhile, a satellite is a complex system composed of a payload and various subsystems. The number of variables for each payload and each subsystem is large and the relationships between them are complex. Therefore, in order to derive a design plan for the entire satellite system within the same platform, it is necessary to consider changes in various parts of the satellite system.

[0005] However, conventional satellite design tools are partially applied to satellite systems, and the design plan is derived by deriving engineering characteristics through design variables for a portion of the satellite system.

[0006] Therefore, these satellite design tools have difficulty in considering changes in other parts of the satellite, and since they can only derive engineering characteristic values ​​of the satellite system according to design variables, it is difficult to directly confirm whether the derived engineering characteristics satisfy the requirements according to the satellite's mission purpose and expected benefits.

[0007] Furthermore, a comprehensive analysis tool for the expected performance of a satellite system, considering the numerous variables and complex relationships within the payload and each subsystem, has been lacking. Conventional design tools can only analyze individual or selected subsystems within a satellite. This makes it difficult to analyze the impact of variables across the entire satellite. Furthermore, it is difficult to analyze development costs, expected revenue, and numerical mission suitability, which are essential considerations for commercial microsatellites, in conjunction with satellite design variables.

[0008] The present invention relates to a satellite design and analysis method and system for deriving a satellite design plan by considering complex relationships and variables for a payload and various subsystems constituting the satellite.

[0009] In addition, the present invention relates to a satellite design and analysis method and system capable of deriving numerical values ​​of engineering characteristics for a satellite according to design variables and confirming whether the derived engineering characteristics satisfy requirements according to mission objectives and expected profits.

[0010] In order to solve the problem discussed above, a satellite design and analysis method according to the present invention may include a step of inputting a mission objective for a satellite and specifying design variables corresponding to the input mission objective; a step of calculating a plurality of engineering characteristics for the satellite based on the design variables; a step of selecting at least one engineering characteristic related to a predetermined requirement among the plurality of engineering characteristics; and a step of calculating a suitability index of the at least one selected engineering characteristic with respect to the requirement and outputting the suitability index so as to evaluate the design variable.

[0011] The satellite design and analysis system according to the present invention may include an input unit for inputting a mission objective for a satellite; and a control unit for specifying design variables corresponding to the mission objective, calculating a plurality of engineering characteristics for the satellite based on the design variables, selecting at least one engineering characteristic related to a predetermined requirement condition among the plurality of engineering characteristics through the input unit, calculating a suitability index of the at least one selected engineering characteristic for the requirement condition, and outputting the suitability index so as to evaluate the design variable.

[0012] A program stored in a computer-readable recording medium according to the present invention is a program stored in a computer-readable recording medium, which is executed by one or more processors in an electronic device, and which may include instructions for performing the steps of: inputting a mission objective for a satellite and specifying a design variable corresponding to the input mission objective; calculating a plurality of engineering characteristics for the satellite based on the design variable; selecting at least one engineering characteristic related to a predetermined requirement among the plurality of engineering characteristics; and calculating a suitability index of the at least one selected engineering characteristic for the requirement and outputting the suitability index to evaluate the design variable.

[0013] According to various embodiments of the present invention, the satellite design and analysis system according to the present invention can quickly derive and analyze a design plan of a microsatellite in the initial design stage, and can derive engineering characteristics according to complex changes in design variables of the orbit, payload, and subsystems constituting the satellite.

[0014] Additionally, according to various embodiments of the present invention, the satellite design and analysis system according to the present invention can be implemented to numerically verify how well a design plan composed of engineering characteristics satisfies requirements according to mission objectives and expected profits.

[0015] Through this, the satellite design and analysis system according to the present invention can efficiently derive optimal design variables by adjusting design variables according to the suitability index, even for satellites with different purposes.

[0016] Figure 1 illustrates a satellite design and analysis system according to the present invention.

[0017] Figure 2 is a flowchart showing a satellite design and analysis method according to the present invention.

[0018] Figures 3 and 4 illustrate an embodiment of calculating engineering characteristics according to design conditions.

[0019] Figures 5 to 9 illustrate an embodiment of calculating a suitability index for a requirement.

[0020] Hereinafter, embodiments disclosed in this specification will be described in detail with reference to the attached drawings. Regardless of the drawing numbers, identical or similar components will be given the same reference numbers, and redundant descriptions thereof will be omitted. The suffixes "module" and "part" used for components in the following description are assigned or used interchangeably only for the convenience of writing the specification, and do not in themselves have distinct meanings or roles. In addition, when describing the embodiments disclosed in this specification, if it is determined that a specific description of a related known technology may obscure the gist of the embodiments disclosed in this specification, a detailed description thereof will be omitted. In addition, the attached drawings are only intended to facilitate easy understanding of the embodiments disclosed in this specification, and the technical ideas disclosed in this specification are not limited by the attached drawings, and should be understood to include all modifications, equivalents, and substitutes included in the spirit and technical scope of the present invention.

[0021] Terms that include ordinal numbers, such as first, second, etc., may be used to describe various components, but the components are not limited by these terms. These terms are used solely to distinguish one component from another.

[0022] When a component is referred to as being "connected" or "connected" to another component, it should be understood that it may be directly connected or connected to that other component, but that there may be other components intervening. Conversely, when a component is referred to as being "directly connected" or "connected" to another component, it should be understood that there are no other components intervening.

[0023] Singular expressions include plural expressions unless the context clearly indicates otherwise.

[0024] In this application, terms such as “include” or “have” are intended to specify the presence of a feature, number, step, operation, component, part or combination thereof described in the specification, but should be understood not to exclude in advance the possibility of the presence or addition of one or more other features, numbers, steps, operations, components, parts or combinations thereof.

[0025] Figure 1 illustrates a satellite design and analysis system according to the present invention.

[0026] Referring to FIG. 1, the satellite design and analysis system (100) according to the present invention can calculate design variables and a plurality of engineering characteristics of a satellite related to a mission objective input for a satellite, and can calculate a suitability index of a plurality of engineering characteristics for a given mission objective and requirements related to expected profits according to the mission objective.

[0027] Here, a satellite may be a vehicle developed to perform various missions, such as exploration, communication relay, and space clearance. Therefore, a satellite may be designed with different engineering characteristics depending on the mission it is intended to perform. Furthermore, a satellite may be designed with different engineering characteristics depending on the payload, subsystems, and detailed modules it carries.

[0028] Design variables are variables identified as affecting the function, performance, and form of a satellite, relative to its mission objectives. They may be set differently depending on the mission and orbit involved in satellite operation, as well as the payload, subsystems, design costs, reliability, and expected revenue associated with each module that composes the satellite. Design variables may include key design variables, other input variables, and external input variables.

[0029] Key design variables are variables that have a major impact on the satellite's mission objectives and the reliability and expected returns associated with the mission objectives. For example, the design variables may include the mission altitude initial value, orbit inclination initial value, orbit analysis period, iterative ground trajectory range, orbit deployment control time, mission start point, mission area location, LTAN, maximum attitude pointing angle, communication system transmit power, communication frequency, communication speed, antenna beamwidth, solar array size, and reaction wheel momentum.

[0030] Other input variables are variables that can affect the satellite's mission objectives, as well as its reliability and expected return associated with those objectives. Compared to key design variables, these variables may have a minimal impact on the satellite's engineering characteristics or be relatively unimportant. For example, these input variables may include repeatable ground trajectory settings, atmospheric density levels, and whether LTAN is adapted.

[0031] External input variables are variables input from the results of other subsystems, and may include, for example, control maximum attitude heading angle, mission maximum visit heading angle, operational speed increment, satellite mass, etc.

[0032] Additionally, engineering characteristics are variables that change in response to design variables, and can be understood as performance that appears according to detailed modules related to the satellite's mission, payload, subsystem, design cost, reliability, and expected revenue.

[0033] For example, engineering characteristics may include control center maximum angle, control target maximum angle, task daily visit time, control communication range, mission center maximum angle, mission target maximum angle, mission area visit cycle, altitude lifetime, Beta angle, power margin, link margin, data margin, reaction wheel momentum / torque margin, attitude pointing accuracy / stability margin, satellite mass, moment of inertia, power available for production, and communication system EIRP&G / T.

[0034] The suitability index may be a comprehensive indicator of how well at least one engineering characteristic aligns with requirements based on mission objectives and expected benefits. In this case, the suitability index may be calculated based on the optimization index for each of at least one engineering characteristic corresponding to each requirement.

[0035] An optimization index can indicate how well each of at least one engineering characteristic derived from design variables satisfies the requirements of the mission objective and expected returns. Therefore, a suitability index can be calculated based on the sum of optimization indices.

[0036] To this end, the satellite design and analysis system (100) may include an input / output unit (110), a storage unit (130), and a control unit (150).

[0037] The input / output unit (110) may include an input module and an output module. At this time, the input module may receive a user command for specifying a predetermined mission purpose, and for example, the input module may refer to a keyboard, mouse, touch pad, button, etc. Accordingly, the control unit (150) may receive a user command related to the mission purpose through the input / output unit (110). At this time, the input module may also receive a user command for specifying an expected profit according to the mission purpose along with the mission purpose.

[0038] Meanwhile, the input module may receive a user command to specify at least one of the design variables and mission conditions for the satellite. In this case, the control unit (150) may specify at least one of the design variables and mission conditions based on the user command.

[0039] Additionally, the output module may be implemented to visually output at least one of the engineering characteristics and the suitability index. Accordingly, the control unit (150) may output at least one of the engineering characteristics and the suitability index through the input / output unit (110).

[0040] The storage unit (130) may include data and commands required for the operation of the satellite design and analysis system (100). For example, the storage unit (130) may store commands for specifying at least one of design variables and requirements corresponding to a mission objective based on user input, and commands for calculating a plurality of engineering characteristics based on the design variables. In addition, the storage unit (130) may store commands for calculating a suitability index of at least one engineering characteristic based on requirements.

[0041] The control unit (150) can control the overall operation of the satellite design and analysis system (100) according to the present invention. To this end, the control unit (150) can include a design module (151) and an analysis module (153).

[0042] The design module (151) can perform overall operations related to the design of a satellite. For example, the design module (151) can specify a mission objective based on user input, determine at least one of the requirements and design variables corresponding to the specified mission objective, and derive engineering characteristics of the satellite based on the design variables.

[0043] The analysis module (153) can perform overall operations related to the analysis and interpretation of engineering characteristics. For example, the analysis module (153) can calculate a suitability index of engineering characteristics based on requirements based on mission objectives and expected benefits.

[0044] At this time, the interpretation module (153) may specify requirements corresponding to the mission purpose according to user input instead of the design module (151).

[0045] In this regard, the satellite design and analysis system (100) may be implemented to be provided through terminals such as tablets, personal computers, and smartphones, and for example, the satellite design and analysis system (100) may be provided in the form of an application or software, or may be provided on a web page.

[0046] Through the above configurations, the satellite design and analysis system (100) according to the present invention can quickly derive and analyze a design plan for a micro-satellite in the initial design stage, and derive engineering characteristics according to complex changes in design variables of the orbit, payload, and subsystems that constitute the satellite.

[0047] In addition, through the above-described configurations, the satellite design and analysis system (100) according to the present invention can be implemented so that a designer can numerically check how well a design plan composed of engineering characteristics is suitable for predetermined requirements according to the mission purpose and expected profit, and through this, the satellite design and analysis system (100) can quickly derive a design plan for a satellite required according to the mission purpose and expected profit even for satellites with different purposes.

[0048] Based on the configuration of the satellite design and analysis system (100) discussed above, the satellite design and analysis method will be described in more detail below. The satellite design and analysis method can be implemented by a program or the like, and thus can be referred to as a control method for a satellite design and analysis tool.

[0049] Figure 2 is a flowchart illustrating a satellite design and analysis method according to the present invention. Figures 3 and 4 illustrate an example of calculating engineering characteristics according to design conditions. Figures 5 to 9 illustrate an example of calculating a suitability index for required conditions.

[0050] Referring to FIG. 2, the satellite design and analysis system (100) according to the present invention inputs a mission objective for a satellite, specifies design variables corresponding to the input mission objective (S100), and based on the previously specified design variables, can calculate a plurality of engineering characteristics for the satellite (S200).

[0051] Specifically, when the satellite's mission objective is specified based on user input, the satellite design and analysis system (100) can specify at least one of the main design variables, other input variables, and external input variables as a design variable in response to the specified mission objective.

[0052] Furthermore, the satellite design and analysis system (100) can, when at least one of a main design variable, other input variable, and external input variable is specified as a design variable in response to a mission objective, calculate one or more engineering characteristics using at least one of the main design variable, other input variable, and external input variable specified in advance, and can sequentially calculate other engineering characteristics linked to one or more of the engineering characteristics calculated in advance using at least one of the main design variable, other input variable, and external input variable and the one or more engineering characteristics calculated in advance.

[0053] At this time, the satellite design and analysis system (100) may also calculate multiple engineering characteristics using a preset numerical approximation model and satellite commodity information. The satellite commodity information may include specifications for the commodity components that constitute the satellite. The numerical approximation model may be implemented to approximate the numerical values ​​generated during the process of calculating the engineering characteristics.

[0054] Furthermore, when design variables for multiple modules constituting a satellite are specified, the satellite design and analysis system (100) can calculate one or more engineering characteristics according to each design variable, and sequentially calculate a plurality of other engineering characteristics linked to each design variable and each engineering characteristic calculated according to each design variable.

[0055] Referring to FIG. 3, for example, the satellite design and analysis system (100) can specify design variables (10a) related to the mission and orbit, design variables (10b) related to the payload, design variables (10c) related to the subsystem, and design variables (10d) related to each of a plurality of detailed modules in response to the mission purpose.

[0056] Accordingly, referring to FIG. 4, the satellite design and analysis system (100) can produce engineering characteristics (30a) related to the mission and orbit, engineering characteristics (30b) related to the payload, engineering characteristics (30c) related to the subsystem, and engineering characteristics (30d) related to each of the plurality of detailed modules, based on the plurality of design variables (10a, 10b, 10c, 10d) specified above.

[0057] At this time, each of the engineering characteristics (30a, 30b, 30c, 30d) can be calculated by further considering design variables related to other modules, and can also be calculated by further considering engineering characteristics calculated by design variables related to other modules.

[0058] Referring to FIGS. 2 and 5, the satellite design and analysis system (100) according to the present invention selects at least one engineering characteristic (30) related to a requirement (50) among a plurality of engineering characteristics (30) (S300), calculates a suitability index (70) of the at least one previously selected engineering characteristic (30) for the requirement (50), and outputs the suitability index (70) to evaluate design variables (S400).

[0059] According to an embodiment, referring to FIG. 6, the satellite design and analysis system (100) may utilize a numerical calculation platform (201) implemented to output a suitability index based on design variables, which are output data from a design module (202), and requirements according to mission objectives.

[0060] In this case, the satellite design and analysis system (100) can generate design variables corresponding to the mission objective according to user input as output data using the design module (202), and input the output data into the engineering characteristic analysis module (205).

[0061] Through this, the satellite design and analysis system (100) can select engineering characteristics corresponding to design variables using the engineering characteristic analysis module (205).

[0062] At this time, the satellite design and analysis system (100) can specify requirements corresponding to the mission purpose according to user input using the requirements analysis module (206), and can calculate a suitability index through the suitability index calculation module (207) based on the engineering characteristics generated by the engineering characteristics analysis module (205) and the requirements generated by the requirements analysis module (206).

[0063] Specifically, the satellite design and analysis system (100) can specify at least one requirement (50) corresponding to the specified mission objective when the mission objective is specified based on user input.

[0064] For example, a satellite design and analysis system (100) may be prepared in advance by matching various different mission objectives and a plurality of requirements (50) corresponding to each mission objective. In addition, at least one engineering characteristic (30) corresponding to each of the plurality of requirements (50) may be matched to each of the plurality of requirements (50).

[0065] Accordingly, the satellite design and analysis system (100) can receive a command from a user to select at least one mission objective among a plurality of mission objectives, and specify at least one requirement (50) matching the selected at least one mission objective.

[0066] Through this, the satellite design and analysis system (100) can extract at least one engineering characteristic (30) matching at least one previously specified requirement (50).

[0067] As another example, the satellite design and analysis system (100) may specify mission objectives and expected returns based on user input. In this case, the satellite design and analysis system (100) may be prepared by pre-matching a plurality of requirements (50) corresponding to each mission objective and expected return, and based on this, a plurality of requirements corresponding to at least one of the previously specified mission objectives and expected returns may be specified.

[0068] Furthermore, the satellite design and analysis system (100) can select at least one engineering characteristic (30) corresponding to at least one requirement (50) specified above.

[0069] As another example with reference to FIG. 7, the satellite design and analysis system (100) is configured such that, based on the mission objective, if a condition (50a) for improving data communication reliability is specified as a requirement (50), then, among a plurality of engineering characteristics (30), a link margin (30a) and a communication speed (30c) can be selected in relation to the specified condition (50a).

[0070] As another example, if a condition (50b) for increasing the amount of relay data per communication is specified as a requirement (50) based on the mission objective of the satellite design and analysis system (100), then, among a plurality of engineering characteristics (30), a link margin (30a) and a communication speed (30c) can be selected in relation to the specified condition (50b).

[0071] Furthermore, the satellite design and analysis system (100) can set at least one of the priorities and numerical ranges for each of the at least one engineering characteristic (30) selected above.

[0072] Here, the priority may represent the priority of each of at least one previously selected engineering characteristic (30) and the priority of each of the plurality of requirement conditions (50) for the requirement condition (50).

[0073] Additionally, the numerical range may represent an adjustable numerical range for each of the values ​​of at least one of the previously selected engineering characteristics (30) and a direction in which the value of each of the at least one engineering characteristic (30) is changed (e.g., increasing or decreasing) to optimize the requirements (50).

[0074] Accordingly, the satellite design and analysis system (100) can determine at least one of the priorities and numerical ranges for each of at least one of the previously selected engineering characteristics (30) based on the previously specified mission objective (or requirement).

[0075] Alternatively, in the case where a plurality of requirements (50) are prepared in advance, the satellite design and analysis system (100) may match at least one of the priorities and numerical ranges with respect to at least one engineering characteristic (30) matched to each of the plurality of requirements (50).

[0076] In such a case, the satellite design and analysis system (100) can extract at least one of the priorities and numerical ranges matching the at least one specified requirement (50) based on the mission objective.

[0077] For example, if a condition for improving data communication reliability is specified as a requirement (50), the satellite design and analysis system (100) may select link margin and communication speed among a plurality of engineering characteristics (30). Accordingly, the satellite design and analysis system (100) may set the link margin to have a higher priority than the communication speed, and may set a numerical range in a direction that increases the link margin and a direction that decreases the communication speed.

[0078] For another example, if the satellite design and analysis system (100) specifies a condition for increasing the amount of relay data per communication as a requirement (50), link margin and communication speed can be selected from among a plurality of engineering characteristics (30). Accordingly, the satellite design and analysis system (100) can set the communication speed to have a higher priority than the link margin, and can set a numerical range in the direction of increasing the communication speed and in the direction of decreasing the link margin.

[0079] Furthermore, the satellite design and analysis system (100) can calculate the importance of each of at least one engineering characteristic (30) selected in advance based on the priority, and calculate the optimization index of each of at least one engineering characteristic based on the numerical range.

[0080] Specifically, the satellite design and analysis system (100) can calculate the importance between at least one engineering characteristic (30) based on the correlation between a plurality of requirements (50) for one of the previously selected at least one engineering characteristic (30) and the priority between the plurality of requirements (50).

[0081] Referring to FIG. 8, for example, it can be confirmed that the priorities (51) among multiple requirements (50) are set in the order of the fourth requirement, the first requirement, the second requirement, the third requirement, and the fifth requirement.

[0082] In addition, it can be confirmed that the correlation with multiple requirements (50) for the first engineering characteristic is set in the order of the third requirement, the second requirement, and the first requirement.

[0083] In addition, the correlation with the multiple requirements (50) for the second engineering characteristic can confirm that the fourth requirement is set.

[0084] In addition, it can be confirmed that the correlation with multiple requirements (50) for the third engineering characteristic is set in the order of the first requirement, the second requirement, and the third requirement.

[0085] In addition, it can be confirmed that the correlation with multiple requirements (50) for the fourth engineering characteristic is set in the order of the second requirement, the third requirement, and the first requirement.

[0086] In addition, the correlation with multiple requirements (50) for the fifth engineering characteristic can confirm that the fifth requirement has been set.

[0087] Accordingly, the satellite design and analysis system (100) can calculate the importance (31) between at least one engineering characteristic (30) selected in the order of the second engineering characteristic, the fourth engineering characteristic, the third engineering characteristic, the first engineering characteristic, and the fifth engineering characteristic.

[0088] Furthermore, the satellite design and analysis system (100) can calculate an optimization index according to the value of each of at least one engineering characteristic (30) calculated according to the design variable based on the numerical range (adjustable numerical range and direction of change of value for optimization) set for each of at least one engineering characteristic (30) previously selected.

[0089] Furthermore, the satellite design and analysis system (100) can apply a weight according to importance (31) to at least one optimization index calculated for each of at least one engineering characteristic (30), and calculate a suitability index (70) by adding up at least one optimization index to which the weight is applied.

[0090] Referring to FIG. 9, for example, it can be confirmed that among the plurality of engineering characteristics, the launch cost per ADR Kg, the launch cost per the same ADR execution range, the maximum mass of one ADR, the total mass that can be ADR, and the total ADR required speed increment are selected according to the conditions for increasing the removable weight per shot, the conditions for increasing the total removable weight, the conditions for increasing the cost efficiency per weight, the conditions for increasing the cost efficiency per mission execution range, and the conditions for reducing the difficulty of mission operation, which are the plurality of requirement conditions (50).

[0091] Accordingly, the satellite design and analysis system (100) can calculate the importance (31) of the engineering characteristic (30) based on the difficulty (55) and priority (51) for correction of the engineering characteristic (30), and can calculate the optimization index (73) of the engineering characteristic (30) based on the numerical range (53).

[0092] Thereafter, the satellite design and analysis system (100) can apply the importance (31) as a weight to the optimization index (73) and add them up to calculate the suitability index (70).

[0093] Through the above configurations, the satellite design and analysis system (100) according to the present invention can quickly derive and analyze a design plan of a commercial micro-satellite suitable for any mission purpose, and can analyze changes in engineering characteristics including the expected performance, required cost, and expected profit of the satellite system according to various design variables constituting the satellite.

[0094] In addition, the satellite design and analysis system (100) according to the present invention can be implemented to numerically confirm how well a design plan composed of engineering characteristics is suitable for requirements according to mission objectives and expected profits, and through this, the satellite design and analysis system (100) can efficiently derive optimal design variables by adjusting design variables according to a suitability index (70).

[0095] Furthermore, the present invention discussed above can be implemented as computer-readable code or instructions on a program-recorded medium. That is, the various control methods according to the present invention can be provided in the form of programs, either integrated or individually.

[0096] Meanwhile, computer-readable media include all types of recording devices that store data that can be read by a computer system. Examples of computer-readable media include hard disk drives (HDDs), solid-state disk drives (SSDs), silicon disk drives (SDDs), ROMs, RAMs, CD-ROMs, magnetic tapes, floppy disks, and optical data storage devices.

[0097] Furthermore, the computer-readable medium may include a storage device and may be a server or cloud storage device accessible via communication. In this case, the computer may download the program according to the present invention from the server or cloud storage device via wired or wireless communication.

[0098] Furthermore, in the present invention, the computer described above is an electronic device equipped with a processor, i.e., a CPU (Central Processing Unit), and there is no particular limitation on its type.

[0099] Meanwhile, the detailed description above should not be construed as limiting in any respect and should be considered illustrative. The scope of the present invention should be determined by a reasonable interpretation of the appended claims, and all modifications within the equivalent scope of the present invention are intended to be included within the scope of the present invention.

Claims

1. A step in which a mission objective for a satellite is input and design variables corresponding to the input mission objective are specified; A step of calculating a plurality of engineering characteristics for the satellite based on the above design variables; A step of selecting at least one engineering characteristic related to a predetermined requirement among the plurality of engineering characteristics; and A satellite design and analysis method, comprising the step of calculating a suitability index of at least one selected engineering characteristic for the above requirements and outputting the suitability index to evaluate the design variables.

2. In the first paragraph, the step of selecting at least one engineering characteristic related to a predetermined requirement among the plurality of engineering characteristics is as follows: A satellite design and analysis method comprising the step of setting at least one of a priority and a numerical range for each of the at least one selected engineering characteristic.

3. In the second paragraph, the step of outputting a suitability index to evaluate the design variables is: A step of calculating an importance for each of the at least one engineering characteristic based on the above priorities; A step of calculating an optimization index of each of the at least one engineering characteristic based on the above numerical range; and A satellite design and analysis method, comprising a step of calculating the suitability index based on the above optimization index and the above importance.

4. In the third paragraph, the step of calculating the importance for each of at least one engineering characteristic based on the priority is: A satellite design and analysis method, wherein the importance of each of the at least one engineering characteristic is calculated by further considering the difficulty of correction of each of the at least one engineering characteristic.

5. In the third paragraph, the step of calculating the suitability index based on the optimization index and importance is as follows: A step of applying a weight according to the importance to at least one optimization index calculated for each of the at least one engineering characteristic; and A satellite design and analysis method comprising a step of calculating the suitability index by summing at least one optimization index to which the weights are applied.

6. In the first paragraph, the step of calculating multiple engineering characteristics for the satellite based on the design variables is as follows: In response to the above mission objective, when at least one of the main design variable, other input variable and external input variable is specified as the design variable, a step of calculating one or more engineering characteristics using at least one of the main design variable, other input variable and external input variable; and A satellite design and analysis method, comprising a step of sequentially calculating other engineering characteristics linked to the calculated one or more engineering characteristics using at least one of the main design variables, the other input variables, and the external input variables, and the calculated one or more engineering characteristics.

7. In the first paragraph, the design variable is, A satellite design and analysis method comprising at least one of a mission altitude initial value, an orbit inclination initial value, an orbit analysis period, an iterative ground trajectory range, an orbit evolution control time, a mission starting point, a mission area position, a LTAN, a maximum attitude pointing angle, a communication system transmit power, a communication frequency, a communication speed, an antenna beamwidth, a solar array size, and a reaction wheel momentum.

8. In the first paragraph, the output variable is A satellite design and analysis method comprising at least one of control center maximum angle, control target maximum angle, task daily visit time, control communication range, mission center maximum angle, mission target maximum angle, mission area visit cycle, altitude lifetime, Beta angle, power margin, link margin, data margin, reaction wheel momentum / torque margin, attitude pointing accuracy / stability margin, satellite mass, moment of inertia, power available for production, and communication system EIRP&G / T.

9. Input section where mission objectives for the satellite are entered; and A satellite design and analysis system comprising a control unit that specifies design variables corresponding to the mission objective, calculates a plurality of engineering characteristics for the satellite based on the design variables, selects at least one engineering characteristic related to a predetermined requirement from among the plurality of engineering characteristics through the input unit, calculates a suitability index of the at least one selected engineering characteristic for the requirement, and outputs the suitability index to evaluate the design variable.

10. A program that is executed by one or more processes in an electronic device and stored in a computer-readable recording medium, The above program is, A step in which a mission objective for a satellite is input and design variables corresponding to the input mission objective are specified; A step of calculating a plurality of engineering characteristics for the satellite based on the above design variables; A step of selecting at least one engineering characteristic related to a predetermined requirement among the plurality of engineering characteristics; and A program stored on a computer-readable recording medium, characterized in that it includes commands for performing a step of calculating a suitability index of at least one selected engineering characteristic for the above requirements and outputting the suitability index to evaluate the design variable.

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