Method and system for deriving mission design plan for orbital service of satellite in consideration of mission efficiency according to costs

Abstract

The present invention provides a mission design plan derivation method comprising: receiving a design variable of a satellite designed to perform a specific orbital service; designing, on the basis of the design variable, the satellite for performing the specific orbital service; calculating design costs required to design the satellite; calculating mission efficiency on the basis of the design costs and service costs for the specific orbital service; and deriving, on the basis of the calculated mission efficiency, a mission design plan of the satellite optimized for the specific orbital service.

Description

Method and system for deriving a mission design plan for satellite on-orbit services considering mission efficiency according to cost

[0001] The present invention relates to a method and system for deriving a mission design plan for an in-orbit service of a satellite that takes into account mission efficiency according to cost.

[0002] Since the inception of space exploration, the production and launch of artificial satellites has exploded. Currently, there are approximately 27,000 space objects in Earth's orbit, of which approximately 7,000 are satellites. Therefore, to curb the growth of space debris in Earth's orbit and improve satellite operational efficiency, satellites are essential for extending their lifespans by providing refueling and repair capabilities, or for decommissioning malfunctioning satellites by moving them to a dead-end orbit. Because these satellites approach target satellites to perform these tasks, they are commonly referred to as "orbital service satellites."

[0003] These orbital service satellites require significantly different propellant masses for their missions, depending on the service target, the maximum number of missions, and the orbital transfer method employed. Furthermore, the size and shape of the orbital service satellites also vary significantly depending on the required propellant mass. Furthermore, the costs of manufacturing and launching a satellite vary significantly depending on its size and shape, making it difficult to balance cost with mission efficiency.

[0004] The present invention relates to a method and system for deriving a mission design plan for designing a satellite to provide a specific orbital service.

[0005] In addition, the present invention relates to a method and system for deriving a mission design plan that calculates mission efficiency by comparing the cost for a specific orbital service with the cost of a satellite designed to provide the service.

[0006] In addition, the present invention relates to a method and system for deriving a mission design plan for deriving a satellite with the highest mission efficiency for a specific orbital service or an orbital service with the highest mission efficiency for a specific satellite.

[0007] In order to solve the problem discussed above, a method for deriving a mission design plan according to the present invention may include the steps of: receiving design variables of a satellite designed to perform a specific orbital service; designing a satellite for performing the specific orbital service based on the design variables and calculating a design cost required for designing the satellite; calculating a mission efficiency for the specific orbital service using the designed satellite based on the calculated design cost and the service cost for the specific orbital service; and deriving a mission design plan for the satellite optimized for the specific orbital service based on the calculated mission efficiency.

[0008] In addition, the mission design plan derivation system according to the present invention includes an input unit for inputting design variables of a satellite designed to perform a specific orbital service; and a control unit for designing a satellite for performing the specific orbital service based on the design variables and calculating a design cost required for designing the satellite, wherein the control unit can calculate a mission efficiency for the specific orbital service using the designed satellite based on the calculated design cost and the service cost for the specific orbital service, and can derive a mission design plan for the satellite optimized for the specific orbital service based on the calculated mission efficiency.

[0009] In addition, 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 includes instructions for performing the steps of: receiving design variables of a satellite designed to perform a specific orbital service; designing a satellite for performing the specific orbital service based on the design variables and calculating a design cost required for designing the satellite; calculating a mission efficiency for the specific orbital service using the designed satellite based on the calculated design cost and the service cost for the specific orbital service; and deriving a mission design plan for the satellite optimized for the specific orbital service based on the calculated mission efficiency.

[0010] According to various embodiments of the present invention, a method and system for deriving a mission design plan can effectively confirm the design costs for various types of satellites capable of performing in-orbit services by designing a satellite that provides a specific in-orbit service according to design variables and calculating the design cost required for designing the satellite.

[0011] In addition, according to various embodiments of the present invention, the mission design plan derivation method and system calculate mission efficiency by comparing the service cost for a specific in-orbit service with the design cost of a satellite designed to provide the service, thereby enabling the design and manufacture of a satellite and the profit and loss of an in-orbit service utilizing the satellite to be grasped at a glance.

[0012] Furthermore, according to various embodiments of the present invention, the mission design plan derivation method and system can efficiently plan a business for an orbital service utilizing a satellite by deriving a design plan of a satellite with the highest mission efficiency for a specific orbital service or a design plan of an orbital service with the highest mission efficiency for a specific satellite.

[0013] Figures 1 and 2 illustrate a mission design plan derivation system according to the present invention.

[0014] Figure 3 is a flowchart showing a method for deriving a mission design plan according to the present invention.

[0015] Figures 4 and 5 illustrate one embodiment of receiving design variables.

[0016] Figure 6 illustrates an example of the relationship between propellant mass and fuel tank capacity by type of thruster.

[0017] Figure 7 illustrates an example of the relationship between satellite size and launch cost for each target orbit.

[0018] Figure 8 illustrates an embodiment showing a relationship to service costs.

[0019] Figure 9 illustrates an embodiment of specifying an optimal task execution sequence.

[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] Figures 1 and 2 illustrate a mission design plan derivation system according to the present invention.

[0026] Referring to FIG. 1, a mission design plan derivation system (100) according to the present invention can design a satellite to perform a specific on-orbit service, and derive a mission design plan of a satellite optimized for a specific on-orbit service based on mission efficiency by considering the design cost for the designed satellite and the service cost for the specific on-orbit service.

[0027] Here, orbital services can refer to a series of services provided by accessing space objects in orbit, such as extending the life of other satellites by accessing them and performing repair and refueling operations, or reducing space debris by moving malfunctioning satellites to graveyard orbits.

[0028] That is, orbital services may include services related to refueling, repairing, and decommissioning satellites (e.g., space stations or small satellites) operating in geostationary orbit or low Earth orbit relative to the Earth or another planet.

[0029] To this end, a satellite can be designed to provide in-orbit services to other satellites operating along a specific orbit. Accordingly, the satellite's payload, thrusters, and shape can be designed based on design variables such as the type of in-orbit service, the altitude of the satellite being serviced, and the number of missions performed.

[0030] Design costs may include the material costs for the components that make up the satellite and the launch costs required for launching the satellite. Here, material costs may include the costs associated with purchasing or processing components for the satellite, while launch costs may include the costs required to launch the satellite, depending on its size.

[0031] Service costs may include fees for providing in-orbit services to other satellites that are part of the service. Additionally, service costs may include the costs of fuel and parts provided to the service recipient in accordance with the in-orbit services.

[0032] Mission efficiency, defined as the ratio of design costs to service costs, can be used as an indicator of the ratio of revenue generated from service costs to design costs. Therefore, mission efficiency is typically characterized as high when design costs are low and service costs are high. Similarly, mission efficiency is typically characterized as low when design costs are high and service costs are low.

[0033] A mission design plan may include information (e.g., design structure, component and material types, etc.) related to the optimized satellite configuration for performing a mission for a specific orbital service. In other words, a mission design plan may include information related to the satellite configuration that yields the highest mission efficiency based on service costs for a specific orbital service.

[0034] Alternatively, the mission design plan may include information related to optimized on-orbit services for a satellite with a specific configuration (e.g., number of missions, type of service, mission sequence, etc.). In such cases, the mission design plan may include information related to the on-orbit services that yield the highest mission efficiency based on design costs for the satellite configuration.

[0035] To this end, the mission design plan derivation system (100) according to the present invention may include an input unit (110), an output unit (120), a control unit (130), and a storage unit (140).

[0036] The input unit (110) is equipped with input modules such as a keyboard, mouse, and touch pad, and can receive commands based on user input. For example, the input unit (110) can input design variables based on user input.

[0037] Here, the design variables may include information related to the on-orbit service (e.g., initial orbit, type of mission, number of mission executions, etc.) and information related to other satellites that are the target of the service (e.g., target orbits in which other satellites are operating, abandoned orbits, etc.).

[0038] These design variables can be input based on a database (230) to be described later. In one embodiment, the input unit (110) is implemented to select one or more of a plurality of predefined service targets based on the database (230), thereby allowing design variables to be input based on user input.

[0039] The output unit (120) is equipped with an output module, such as a display screen, and can output certain information so that a user can visually confirm it. For example, the output unit (120) can output information related to the shape of a satellite designed according to design variables, and can output the shape of the satellite based on the design variables, the mission efficiency for in-orbit services, and the mission design plan.

[0040] At this time, the output unit (120) may output predetermined information so that the user can check the shape of the satellite or information related to the orbital service by listing text or predetermined numerical values, or may output predetermined information so that the user can check the shape of the satellite or information related to the orbital service based on a predetermined graphic source.

[0041] The control unit (130) can control the overall operation of the mission design plan derivation system (100) according to the present invention. For example, the control unit (130) can receive design variables based on user input and design a satellite for a specific orbital service based on the design variables. Furthermore, the control unit (130) can calculate the mission efficiency of a previously designed satellite for a specific orbital service and derive an optimized mission design plan based on the calculated mission efficiency.

[0042] The storage unit (140) can store data and commands necessary for the operation of the mission design derivation system (100) according to the present invention. For example, the storage unit (140) can store information related to orbital services (e.g., mission type and number of missions performed, etc.), information related to other satellites corresponding to the service target (e.g., type, mass and target orbit of other satellites, etc.), and information related to the design of satellites (e.g., type of payload, type of thruster, type of satellite and type of material, etc.).

[0043] In this regard, specifically, the storage unit (140) may include a satellite analysis module (210), a mission analysis module (220), and a database (230).

[0044] The satellite analysis module (210) can be implemented to calculate the design cost for the satellite based on the performance, size and cost of commercial components for the satellite and the commercial cost for launch services for the satellite.

[0045] That is, the satellite analysis module (210) can estimate the initial orbit according to the orbital service specified according to the design variables, the mass of the propellant required for the satellite according to the design variables, and the manufacturing design cost of the satellite.

[0046] To this end, the satellite analysis module (210) receives design variables according to user input, and information necessary to design the shape of the satellite based on the received design variables can be stored.

[0047] The mission analysis module (220) can store information necessary to calculate the mission efficiency for a satellite designed by the satellite analysis module (210) and a specific orbital service, and to derive an optimal mission design plan based on the mission efficiency.

[0048] The database (230) may store general information related to a service target requiring in-orbit services. For example, the database (230) may store information related to other satellites, space debris, etc., which require various in-orbit services as service targets. In particular, depending on the type of in-orbit service, the database may store information related to the target orbit for accessing the service target, service provision time, fuel supply amount, orbital disposal, and parts (or materials) required for repair.

[0049] In this regard, referring to FIG. 2, the design variable input module (211) of the satellite analysis module (210) can be implemented so that design variables are input based on a database (230).

[0050] Accordingly, the propellant mass calculation module (221) of the mission analysis module (220) can be implemented to calculate the mass of the propellant required to perform a specific orbital service for the service target based on design variables input based on the database (230).

[0051] At this time, the service target may be one other satellite (or space debris), or may include at least one of multiple other satellites and space debris.

[0052] Next, the thruster shape design module (212) of the satellite analysis module (210) can be implemented to specify the shape of the thruster to be mounted on the satellite based on the previously input design variables and the previously calculated mass of the propellant.

[0053] In addition, the satellite shape design module (213) of the satellite analysis module (210) can be implemented so that the type of payload to be mounted on the satellite and the shape of the satellite are specified based on the thruster shape specified in advance.

[0054] In addition, the design cost calculation module (214) of the satellite analysis module (210) can be implemented to calculate the design cost required for a previously designed satellite, and the service cost calculation module (222) of the mission analysis module (220) can be implemented to calculate the service cost for an in-orbit service based on the database (230) and previously input design variables.

[0055] Next, the mission efficiency calculation module (223) of the mission analysis module (220) can be implemented to calculate the mission efficiency based on the previously calculated design cost and service cost, and the mission design plan derivation module (224) can be implemented to derive an optimized mission design plan based on the previously calculated mission efficiency.

[0056] Based on the configuration of the mission design plan derivation system (100) discussed above, the mission design plan derivation method will be described in more detail below.

[0057] Figure 3 is a flowchart illustrating a method for deriving a mission design plan according to the present invention. Figures 4 and 5 illustrate an embodiment of receiving design variables. Figure 6 illustrates an embodiment of showing the relationship between propellant mass and fuel tank capacity by thruster type. Figure 7 illustrates an embodiment of showing the relationship between satellite size and launch cost by target orbit. Figure 8 illustrates an embodiment of showing the relationship regarding service costs. Figure 9 illustrates an embodiment of specifying an optimal mission execution order.

[0058] Referring to FIG. 3, the mission design derivation system (100) according to the present invention receives design variables of a satellite designed to perform a specific orbital service (S100), designs a satellite to perform an orbital service based on the previously received design variables, and calculates a design cost required for designing the satellite (S200).

[0059] Specifically, the mission design plan derivation system (100) can receive information related to the target orbit and information related to the type of orbital service to be provided for the target orbit as design variables based on a pre-established database.

[0060] Referring to FIG. 4, for example, the mission design derivation system (100) can receive, as design variables (10), the type of on-orbit service (231) (e.g., fuel supply, repair and disposal of other satellites, etc.), the number of missions performed for on-orbit service (232), and one or more target orbits (233) (e.g., low Earth orbit, geostationary orbit) to which the on-orbit service will be provided.

[0061] As another example, the mission design derivation system (100) may receive the type of on-orbit service, the number of mission executions, the fuel (or parts and materials, etc.) provided to the target satellite according to the on-orbit service, the amount of supplies per mission execution cycle, and the target orbit as design variables.

[0062] As another example with reference to FIG. 5, the mission design plan derivation system (100) can receive information related to one or more service targets (20a) corresponding to a user input among a plurality of service targets (20) stored in a database (230).

[0063] In this case, the mission design derivation system (100) can receive, as design variables, information related to one or more service targets (20a) received according to user input, such as the type of on-orbit service (e.g., fuel supply service (231a)), target orbit (e.g., geostationary orbit (233a)), and number of mission executions. In this case, the number of mission executions may be the number of service targets (20) received according to user input.

[0064] Furthermore, the mission design plan derivation system (100) can specify a payload to be mounted on a satellite based on the type of on-orbit service according to previously received design variables, and calculate the mass of propellant required to operate the previously specified payload and perform on-orbit service according to previously received design variables.

[0065] For example, if the type of on-orbit service according to the previously received design variables is a discard service, the mission design derivation system (100) can specify a payload to be mounted on the satellite, such as a robot arm or a net, and calculate the mass of the propellant by considering the mass of the specified payload, the mass of the satellite, the target orbit for approaching another satellite corresponding to the service target according to the on-orbit service, the mass of the other satellite, and the number of mission executions.

[0066] That is, the mission design derivation system (100) can calculate the mass of the propellant for providing an on-orbit service according to the design variables based on the speed increment for approaching the target orbit, the mass of the satellite, the mass of the satellite to be serviced, and the number of mission executions.

[0067] As another example, if the type of on-orbit service according to the previously received design variables is a fuel supply service, the mission design derivation system (100) can specify a payload to be loaded on the satellite so that a separate fuel tank for supplying fuel to another satellite is installed, and calculate the mass of the propellant by considering the mass of the specified payload and the fuel supplied to the payload, the mass of the satellite, the mass of the satellite to be serviced, the speed increment for approaching the service target orbit, and the number of mission executions.

[0068] Furthermore, the mission design plan derivation system (100) can specify the shape of the satellite thruster based on the mass of the propellant calculated in advance, and can specify the shape of the satellite based on the shape of the thruster calculated in advance.

[0069] For example, the mission design derivation system (100) can determine the size and type of the thruster by considering the capacity of the fuel tank according to the mass of the propellant calculated in advance, and can calculate the size of the satellite based on the size and type of the specified thruster.

[0070] As another example, the mission design derivation system (100) can determine the size and type of the thruster by considering the capacity of the fuel tank according to the mass of the propellant calculated in advance, and can calculate the size of the satellite by considering the size and type of the specified thruster and the target orbit for providing orbital services.

[0071] As another example with reference to FIG. 6, the mission design derivation system (100) may specify the type of thruster based on the mass of the propellant calculated in advance, and may also specify the size of the thruster corresponding to the mass of the propellant calculated in advance based on the size of the thruster determined in advance for each propellant mass level.

[0072] At this time, the mission design plan derivation system (100) can determine in advance the size of the thruster according to the type of thruster and the propellant mass level, and can specify the size of the thruster corresponding to the propellant mass calculated in advance based on the size of the thruster according to the propellant mass level related to the type of thruster specified in advance.

[0073] In one embodiment, the thruster size for each propellant mass level, as described above, may be determined based on information from commercial products.

[0074] Furthermore, the mission design plan derivation system (100) can determine the design cost required for designing a satellite by calculating the material cost required to manufacture a satellite having a previously specified satellite shape and the launch cost required to launch the manufactured satellite.

[0075] For example, the mission design derivation system (100) can calculate material costs based on the types and quantities of parts and materials required to manufacture a satellite having a previously specified payload and thruster, and can calculate launch costs according to the previously calculated satellite size based on launch costs according to the size of the satellite determined in advance.

[0076] Accordingly, the mission design plan derivation system (100) can calculate the design cost by adding the material cost and the launch cost.

[0077] Referring to FIG. 7, as another example, the mission design derivation system (100) can calculate the launch cost according to the size of the satellite calculated in advance based on the launch cost according to the size of the satellite determined in advance according to the target orbit according to the orbital service.

[0078] That is, the mission design plan derivation system (100) calculates the launch cost for a previously designed satellite by considering the launch cost for each size of a satellite determined in advance for a low orbit when the target orbit is a low orbit, and calculates the launch cost for a previously designed satellite by considering the launch cost for each size of a satellite determined in advance for a geostationary orbit when the target orbit is a geostationary orbit.

[0079] In one embodiment, the launch cost for each satellite size, as described above, may be determined based on information on commercial products.

[0080] Accordingly, the mission design plan derivation system (100) can calculate the design cost by adding the material cost and the launch cost.

[0081] As another example, the mission design plan derivation system (100) can calculate the material cost according to the size of the satellite calculated in advance based on the material cost according to the size of the satellite determined in advance, and can calculate the launch cost according to the size of the satellite calculated in advance based on the launch cost according to the size of the satellite determined in advance.

[0082] Accordingly, the mission design plan derivation system (100) can calculate the design cost by adding the material cost and the launch cost.

[0083] Referring again to FIG. 3, the mission design derivation system (100) according to the present invention can calculate the mission efficiency for a specific orbital service using a previously designed satellite based on the previously calculated design cost and the service cost for a specific orbital service (S300).

[0084] Specifically, the mission design plan derivation system (100) can calculate a service cost as a price for providing an on-orbit service according to previously received design variables.

[0085] Referring to (a) and (b) of FIG. 8, for example, if the type of orbital service according to the previously received design variables is a decommissioning service, the mission design plan derivation system (100) can calculate the service cost based on the mass (a) of another satellite corresponding to the service target and the difference (b) between the target orbit and the predetermined decommissioning orbit.

[0086] That is, the mission design plan derivation system (100) can increase the service cost as the mass of the satellite (or space debris) corresponding to the service target increases and the orbital difference increases, and can decrease the service cost as the mass of the satellite (or space debris) corresponding to the service target decreases and the orbital difference decreases.

[0087] In one embodiment, the relationship between the service cost and the mass and orbital difference of the service target may be determined based on information from commercial services.

[0088] Referring to (c) of FIG. 8, as another example, the mission design plan derivation system (100) can calculate the service cost based on the mass of fuel supplied to another satellite corresponding to the service target when the type of on-orbit service according to the previously received design variables is a fuel supply service.

[0089] In one embodiment, the relationship between the service cost and the mass of fuel supplied to the service target may be determined based on information from commercial services.

[0090] Referring to (d) of FIG. 8, for another example, if the type of on-orbit service according to the previously received design variables is a repair or parts (or materials) supply service, the service cost can be calculated based on the mass of the parts (or materials) supplied (or provided) to another satellite corresponding to the service target.

[0091] In one embodiment, the relationship between the service cost and the mass of the part (or material) supplied to the service target may be determined based on information from commercial services.

[0092] Furthermore, the mission design plan derivation system (100) can compare the previously calculated design cost and service cost and calculate mission efficiency based on the comparison result.

[0093] For example, the mission design plan derivation system (100) can calculate the ratio of design cost to service cost as mission efficiency by dividing the service cost by the design cost.

[0094] Accordingly, the mission design plan derivation system (100) can be understood to have a higher profit / loss ratio as the mission efficiency is calculated as a higher value, and a lower profit / loss ratio as the mission efficiency is calculated as a lower value.

[0095] Referring again to FIG. 3, the mission design plan derivation system (100) according to the present invention can derive a mission design plan of a satellite optimized for a specific orbital service based on the previously calculated mission efficiency (S400).

[0096] Specifically, the mission design plan derivation system (100) can adjust at least some of the components of a satellite designed to provide a specific orbital service (e.g., propellant size, payload size, type, etc.) to check the mission efficiency of each of a plurality of different satellites related to a specific orbital service, compare the calculated mission efficiency for each of the plurality of satellites, and derive information related to a satellite with the highest mission efficiency as a mission design plan for a specific orbital service.

[0097] For example, the mission design plan derivation system (100) can derive information (e.g., payload type, thruster size, satellite size, etc.) related to the satellite with the highest mission efficiency for the same orbital service according to different design variables, thereby deriving a mission design plan including a satellite optimized for a specific orbital service according to design variables.

[0098] To this end, the mission design derivation system (100) can identify the satellite with the highest mission efficiency by comparing the mission efficiencies calculated for each of multiple satellites with different design costs for the same service cost.

[0099] In such cases, the mission design may include information regarding the satellite with the highest mission efficiency based on the design parameters, along with information regarding the previously specified on-orbit services.

[0100] As another example, the mission design derivation system (100) can derive a mission design including an optimized orbital service for a specific satellite according to design variables by deriving information related to the orbital service with the highest mission efficiency (e.g., number of missions performed, target orbit, etc.) based on a specific satellite according to design variables.

[0101] To this end, the mission design derivation system (100) can identify the orbital service with the highest mission efficiency by comparing the mission efficiencies calculated for each of multiple orbital services with different service costs for the same design cost.

[0102] In such cases, the mission design may include information related to the orbital service with the highest mission efficiency based on the design parameters, along with information related to the previously specified satellite.

[0103] Furthermore, the mission design plan derivation system (100) can arbitrarily designate a mission execution order for each of two or more service targets received as design variables among multiple service targets stored in a database, and calculate mission efficiency according to the previously arbitrarily designated mission execution order, thereby calculating an optimal mission execution order for two or more service targets.

[0104] Referring to FIG. 9, for example, the mission design plan derivation system (100) can arbitrarily designate a mission execution order (31, 32) for two or more service targets received as design variables, and calculate mission efficiency (41, 42) according to the previously designated mission execution order.

[0105] At this time, the mission execution order (31, 32) may be specified as a plurality of mission execution orders (31, 32) according to the number of all cases that do not overlap for two or more service targets, or at least some of the plurality of mission execution orders (31, 32) may be specified.

[0106] Accordingly, the mission design plan derivation system (100) can calculate the mission efficiency (41, 42) of each of the plurality of mission execution sequences (31, 32) (or, at least, some of the mission execution sequences (31, 32)), and, among the calculated plurality (or, at least some) of the mission efficiencies (41, 42), can specify the mission execution sequence with the highest mission efficiency as the optimal visit sequence.

[0107] Through the above configurations, the mission design derivation system (100) according to the present invention designs a satellite that provides a specific orbital service according to design variables, and calculates the design cost required for satellite design, thereby effectively confirming the design cost for various types of satellites capable of performing orbital services.

[0108] In addition, the mission design derivation system (100) according to the present invention calculates mission efficiency by comparing the service cost for a specific orbital service with the design cost of a satellite designed to provide the service, thereby enabling the profit and loss of the design and production of the satellite and the orbital service utilizing the satellite to be grasped at a glance.

[0109] Furthermore, the mission design plan derivation system (100) according to the present invention can efficiently plan a business for an orbital service utilizing a satellite by deriving a design plan of a satellite with the highest mission efficiency for a specific orbital service or a design plan of an orbital service with the highest mission efficiency for a specific satellite.

[0110] Furthermore, the present invention discussed above can be implemented as a program executed by one or more processes in an electronic device and stored in a computer-readable recording medium.

[0111] Accordingly, the present invention 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 integrated or individual programs.

[0112] 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.

[0113] 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.

[0114] 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.

[0115] 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 of receiving design parameters of a satellite designed to perform a specific orbital service; A step of designing a satellite to perform the specific orbital service based on the above design variables and calculating the design cost required for designing the satellite; A step of calculating the mission efficiency for the specific orbital service using the designed satellite based on the calculated design cost and the service cost for the specific orbital service; and A method for deriving a mission design plan, comprising a step of deriving a mission design plan of the satellite optimized for the specific orbital service based on the calculated mission efficiency.

2. In the first paragraph, the step of receiving the design variable is: A method for deriving a mission design plan, which receives, as design variables, information related to a target orbit according to the specific orbital service and information related to the type of orbital service to be provided for the target orbit, based on a pre-established database.

3. In the first paragraph, the step of calculating the design cost is as follows: A step of specifying a payload to be mounted on the satellite based on the type of on-orbit service according to the received design variables; and A method for deriving a mission design plan, comprising the step of calculating the mass of propellant required to operate the specified payload and perform the specified on-orbit service according to the received design variables.

4. In the third paragraph, the step of calculating the design cost is as follows: A step of specifying the shape of the thruster of the satellite based on the mass of the propellant produced above; and A method for deriving a mission design plan, further comprising a step of specifying a shape of the satellite based on the generated thruster shape.

5. In the fourth paragraph, the step of calculating the design cost is as follows: A step of calculating the material cost required to manufacture a satellite having the shape of the above-mentioned specific satellite and the launch cost required to launch the satellite; and A method for deriving a mission design plan, further comprising the step of specifying the design cost required for designing the satellite based on the material cost and the launch cost.

6. In the first paragraph, the step of calculating the mission efficiency is as follows: A method for deriving a mission design plan, comprising the step of calculating a service cost as a consideration for providing the specific orbital service according to the received design variables.

7. In the first paragraph, the step of calculating the mission efficiency is as follows: A step of comparing the above design cost and the above service cost; and A method for deriving a mission design plan, comprising a step of calculating mission efficiency based on the above comparison results.

8. In the first paragraph, the step of deriving the mission design plan is: A step of arbitrarily designating a task execution order for each of two or more service targets received as the design variables among a plurality of service targets stored in a pre-established database, and calculating the task efficiency according to the arbitrarily designated task execution order; A method for deriving a mission design plan, comprising a step of deriving an optimal mission execution order for two or more service targets based on the mission efficiency derived above.

9. Input section into which design parameters of a satellite designed to perform a specific orbital service are entered; and Based on the above design variables, a control unit is included that designs a satellite to perform the specific orbital service and calculates the design cost required for designing the satellite. The above control unit, A mission design plan derivation system which calculates a mission efficiency for the specific on-orbit service using the designed satellite based on the calculated design cost and the service cost for the specific on-orbit service, and derives a mission design plan for the satellite optimized for the specific on-orbit service based on the calculated mission efficiency.

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 of receiving design parameters of a satellite designed to perform a specific orbital service; A step of designing a satellite to perform the specific orbital service based on the above design variables and calculating the design cost required for designing the satellite; A step of calculating the mission efficiency for the specific orbital service using the designed satellite based on the calculated design cost and the service cost for the specific orbital service; and A program stored on a computer-readable recording medium, characterized in that it includes commands for performing a step of deriving a mission design plan of the satellite optimized for the specific orbital service based on the calculated mission efficiency.

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