JP2010086092A - Satellite design support apparatus, satellite design support program, and satellite design support method - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an apparatus and software for facilitating artificial satellite mounting apparatus arrangement design. <P>SOLUTION: A two-dimensional (2D) display part 111 displays a development figure, where an artificial satellite model with a mounting apparatus arranged therein is developed in a 2D coordinate system, in a display device. A model editing part 120 operates an input device such as a keyboard and a mouse, so as to edit the arrangement of the mounting apparatus of the artificial satellite model, etc., concerning the development figure displayed by the 2D display part 111. A temperature calculating part 141 calculates, based on information edited by the model editing part 120, an incident amount of heat to the artificial satellite model when an artificial satellite is moved on an orbit, and calculates the temperature of the mounting apparatus of the artificial satellite model at a prescribed position. Then, the 2D display part 111 displays the calculated temperature of the mounting apparatus of the artificial satellite model in the display device. The above processing is repeated, so as to perform the artificial satellite mounting apparatus arrangement design. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to a satellite design support apparatus such as a CAD (Computer Aided Design) apparatus for designing an artificial satellite. In particular, the present invention relates to a satellite design support device such as a CAD device for supporting the conceptual design of the arrangement of equipment mounted on an artificial satellite. The present invention provides support so that, for example, a user can optimize the structure shape of a satellite and the arrangement / shape / characteristics of onboard equipment from the viewpoint of the heat balance from each structure panel.

As a thermal analysis method and apparatus that can contribute to the arrangement design of onboard equipment for an artificial satellite, for example, there is a general-purpose analysis tool that uses an analysis method that is performed by subdividing the shape elements described in Patent Document 1.
Japanese Patent Laid-Open No. 04-007675

  When the general-purpose analysis tool as described above is used, the on-board equipment mounted on the satellite model must be defined according to the general-purpose shape element definition method. For this reason, the operation for creating the satellite model takes a lot of time and effort, and a certain level of skill is required. Therefore, general-purpose analysis tools are suitable for use in the detailed design stage where detailed shape definition is required to obtain calculation accuracy, but rough calculation is performed in the initial conceptual design stage where details are not determined. This is not suitable for the purpose of quickly performing data editing operations because more data editing operations are required than necessary.

  In general-purpose analysis tools, an artificial satellite model is handled in subdivided shape units, not in units of installed devices. For this reason, when a general-purpose analysis tool determines the placement of mounted devices by trial and error, it is not easy to edit not only addition / deletion of mounted devices but also movement and size change.

  Furthermore, the structure of an artificial satellite generally has a polyhedral structure composed of honeycomb panels. For this reason, the amount of heat incident on the mounted device from the celestial body greatly depends on the geometrical relationship between the orientation of each panel and the position of the celestial body that change from moment to moment. Therefore, when performing trial and error on the placement of mounted devices, the placement across different panels is frequently performed in consideration of the heat balance in units of panels. The editing work for trying many analysis cases for such a purpose is very complicated with the editing function of a general-purpose analysis tool that can generally be handled only by a three-dimensional coordinate system. In addition, there is nothing that can immediately use the placement result of the on-board equipment in the layout design by associating it with the relative relationship with the position and attitude of the satellite itself and the position of the celestial body.

  An object of the present invention is to provide, for example, an apparatus and software for facilitating the design of an onboard equipment for an artificial satellite.

The satellite design support apparatus according to the present invention is, for example, a satellite design support apparatus that supports placement design of an installed device of an artificial satellite,
A two-dimensional display unit that displays on a display device a development view in which a satellite model in which the on-board equipment is arranged is developed in a two-dimensional coordinate system;
A model editing unit that edits setting information of at least one of an arrangement, a shape, and a size of the mounted device of the artificial satellite model by operating a development view displayed by the two-dimensional display unit via an input device;
Based on the setting information of the device equipped with the satellite model edited by the model editing unit, the amount of heat incident on the satellite model when the satellite indicated by the satellite model moves in a predetermined orbit is calculated. A temperature calculation unit for calculating a temperature of the mounted device of the artificial satellite model at a predetermined time after the start of movement in the predetermined orbit by a processing device;
And a result display unit that displays the temperature of the on-board device of the satellite model calculated by the temperature calculation unit as result information on a display device.

The model editing unit sets the calorific value of the on-board equipment at each time after the artificial satellite starts moving,
The temperature calculation unit calculates a temperature of the mounted device of the artificial satellite model at the predetermined position based on an amount of heat incident on the artificial satellite model and the calorific value.

The model editing unit edits the setting information of the onboard device including the solar battery paddle, and sets the power balance of the onboard device,
The satellite design support device further includes:
Based on the power balance of the on-board equipment set by the model editing unit, a power balance calculation for calculating a power balance of the artificial satellite model at a predetermined position when the artificial satellite moves in the predetermined orbit by a processing device Part
The result display unit displays the power balance calculated by the power balance calculation unit as result information.

The model editing unit sets the power consumption of the mounted device at each time after the start of movement of the artificial satellite,
The power balance calculation unit calculates the power balance of the artificial satellite model at the predetermined position based on the power balance of the mounted device and the power consumption set by the model editing unit.

The satellite design support device further includes:
A setting chart display unit for displaying a time chart for setting at least one of the heat generation amount and power consumption of the mounted device on a display device;
The model editing unit sets at least one of the heat generation amount and power consumption of the mounted device at each time after the start of movement of the artificial satellite by operating the time chart displayed by the setting chart display unit. And
The result display unit displays the result information as a graph side by side or overlaid with the time chart displayed by the setting chart display unit.

The result display unit displays a three-dimensional animation of the artificial satellite moving in the predetermined orbit and the result information at a predetermined time after the artificial satellite starts moving in the predetermined orbit indicated by the three-dimensional animation. It is characterized by doing.

The result display unit displays the artificial satellite moving in the predetermined orbit so that the portion of the artificial satellite that is exposed to sunlight and the portion that is not irradiated can be identified.

When displaying the result information as a graph, the result display unit indicates the result information at a predetermined time after the start of movement of the artificial satellite in the predetermined orbit indicated by the three-dimensional animation in the graph. It is characterized by highlighting the part.

The model editing unit sets mass characteristics including at least one of a mass of mass points to be added, an addition position, a density, and an area density for the mounted device,
The satellite design support device further includes:
Based on the shape and size of the on-board equipment and the mass characteristics set by the model editing unit, the mass characteristics including at least one of inertia ratio, inertial product, mass, and barycentric coordinates of the satellite model A mass characteristic calculation unit for calculating
The result display unit displays the mass characteristic of the artificial satellite model calculated by the mass characteristic calculation unit.

The satellite design support device further includes:
The satellite model on which the mounted device displayed by the two-dimensional display unit is arranged is displayed three-dimensionally, and the operating coverage surface of the mounted device operated by the actuator of the artificial satellite indicated by the artificial satellite model is displayed on the display device. A three-dimensional display unit is provided.

The three-dimensional display unit is characterized in that the visual field range from the mounted device is superimposed on the artificial satellite model together with the mounted device.

The satellite design support program according to the present invention is, for example, a satellite design support program that supports onboard equipment layout design of an artificial satellite,
A two-dimensional display process for displaying a development view in which a satellite model in which an on-board device is arranged is developed in a two-dimensional coordinate system;
A model editing process for editing setting information of at least one of the arrangement, shape, and size of the mounted device of the artificial satellite model by manipulating the developed view displayed in the two-dimensional display process;
The amount of heat incident on the satellite model when the artificial satellite indicated by the artificial satellite model moves in a predetermined orbit is calculated based on the setting information of the onboard device of the artificial satellite model edited by the model editing process. A temperature calculation process for calculating a temperature of the mounted device of the artificial satellite model at a predetermined time after the start of movement in the predetermined orbit,
And a result display process for displaying the temperature of the artificial satellite model calculated in the temperature calculation process as result information.

In the model editing process, for each time after the start of movement of the artificial satellite, set the heat generation amount of the onboard equipment,
In the temperature calculation process, the temperature of the equipment mounted on the artificial satellite model at the predetermined position is calculated based on the amount of heat incident on the artificial satellite model and the calorific value.

In the model editing process, the setting information of the mounted device including the solar battery paddle is edited, and the power balance of the mounted device is set,
The satellite design support program further includes:
Based on the power balance of the on-board equipment set in the model editing process, a power balance calculation for calculating the power balance of the artificial satellite model at a predetermined position when the artificial satellite moves in the predetermined orbit by a processing device Let the computer execute the process,
In the result display process, the power balance calculated in the power balance calculation process is displayed as result information.

In the model editing process, for each time after the start of movement of the artificial satellite, set the power consumption of the on-board equipment,
In the power balance calculation process, the power balance of the artificial satellite model at the predetermined position is calculated based on the power balance of the mounted device and the power consumption set in the model editing process.

The satellite design support program further includes:
Causing the computer to execute a setting chart display process for displaying a time chart for setting at least one of the heat generation amount and power consumption of the mounted device;
In the model editing process, by operating the time chart displayed in the setting chart display process, at least one of the heat generation amount and power consumption of the mounted device is set for each time after the artificial satellite starts moving. And
In the result display process, the result information is displayed as a graph side by side or superimposed on the time chart displayed in the setting chart display process.

In the result display process, the three-dimensional animation of the artificial satellite moving in the predetermined orbit and the result information at a predetermined time after the artificial satellite starts moving in the predetermined orbit indicated by the three-dimensional animation are displayed. It is characterized by doing.

In the result display process, together with the artificial satellite moving in the predetermined orbit, a portion of the artificial satellite that is exposed to sunlight and a portion that is not irradiated are displayed so as to be distinguishable.

In the result display process, when the result information is displayed as a graph, the result information at a predetermined time after the start of movement of the artificial satellite in the predetermined orbit indicated by the three-dimensional animation is displayed. It is characterized by highlighting the part.

In the model editing process, a mass characteristic including at least one of the mass of the mass point to be added, the addition position, the density, and the surface density is set for the mounted device,
The satellite design support program further includes:
Based on the shape and size of the on-board equipment and the mass characteristics set in the model editing process, the mass characteristics including at least one of inertia ratio, inertial product, mass, and barycentric coordinates of the satellite model The computer executes mass characteristic calculation processing for calculating
In the result display process, the mass characteristic of the satellite model calculated in the mass characteristic calculation process is displayed.

The satellite design support program further includes:
The artificial satellite model in which the on-board equipment to be displayed in the two-dimensional display processing is arranged is three-dimensionally displayed, and the operation coverage surface of the on-board equipment operated by the artificial satellite actuator indicated by the artificial satellite model is displayed on the display device. A three-dimensional display process is executed by a computer.

In the three-dimensional display process, the visual field range from the mounted device is superimposed on the artificial satellite model together with the mounted device.

The satellite design support method according to the present invention is, for example, a satellite design support method that supports placement design of an onboard device for an artificial satellite,
A two-dimensional display step in which the display device displays a development view in which the satellite model in which the on-board equipment is arranged is developed in a two-dimensional coordinate system;
A model editing step in which the input device edits the setting information of at least one of the arrangement, shape, and size of the device on which the artificial satellite model is mounted by operating the development view displayed in the two-dimensional display step;
The processor enters the artificial satellite model when the artificial satellite indicated by the artificial satellite model moves in a predetermined orbit based on the setting information of the equipment equipped with the artificial satellite model edited in the model editing step. A temperature calculation step of calculating an amount, and calculating a temperature of a mounted device of the artificial satellite model at a predetermined time after the start of movement in the predetermined orbit,
The display device includes a result display step of displaying the temperature of the artificial satellite model calculated in the temperature calculation step as result information.

  According to the satellite design support apparatus according to the present invention, it is possible to design the placement of artificial satellites by manipulating a two-dimensionally displayed artificial satellite model development view, and to confirm the heat balance of the design result. Therefore, it is possible to facilitate the arrangement design of the onboard equipment for the artificial satellite.

  In the following description, the processing device is a CPU 911 or the like which will be described later. The storage device is a ROM 913, a RAM 914, a magnetic disk 920, etc., which will be described later. Input devices are a keyboard 902, a mouse 903, a communication board 915, and the like, which will be described later. The display device is an LCD 901 described later. That is, the processing device, the storage device, the input device, and the display device are hardware.

Embodiment 1 FIG.
FIG. 1 is a functional block diagram showing the functions of a satellite design support apparatus 100 that supports the placement design of onboard equipment for artificial satellites.
The satellite design support apparatus 100 includes a display unit 110 (result display unit), a model editing unit 120, an orbit calculation unit 130, and a result calculation unit 140.
The display unit 110 displays an artificial satellite model (artificial satellite structure model) on which the on-board device is arranged on a display device. Here, the artificial satellite model is a virtual artificial satellite in which the artificial satellite is represented by a three-dimensional mathematical model. The display unit 110 displays the result calculated by the result calculation unit 140 described later on the display device. The display unit 110 includes a two-dimensional display unit 111, a three-dimensional display unit 112, a space model display unit 113, a setting chart display unit 114, and a transport dialog display unit 115. Each function of the display unit 110 will be described later.
The model editing unit 120 operates the artificial satellite model on which the on-board device displayed by the display unit 110 is arranged via the input device, thereby obtaining the setting information of the on-satellite model and the on-board device arranged in the artificial satellite model. To edit.
The orbit calculation unit 130 calculates the position (orbit) of the artificial satellite indicated by the artificial satellite model based on the orbital dynamics.
The result calculation unit 140 is based on the artificial satellite model edited by the model editing unit 120 and the setting information of the on-board equipment, and the mass characteristics of the artificial satellite model and the orbit calculated by the orbit calculation unit 130 when the artificial satellite moves. The equipment temperature and power balance of the artificial satellite model at a predetermined time position in the orbit are calculated by the processing device as result information. The result calculation unit 140 includes a temperature calculation unit 141, a power balance calculation unit 142, and a mass characteristic calculation unit 143. Each function of the result calculation unit 140 will be described later.

Each function of the display unit 110 will be described. As described above, the display unit 110 includes the two-dimensional display unit 111, the three-dimensional display unit 112, the space model display unit 113, the setting chart display unit 114, and the transport dialog display unit 115.
The two-dimensional display unit 111, the three-dimensional display unit 112, and the space model display unit 113 display a graphical editing window for editing the artificial satellite model and the mounted device, respectively. That is, the satellite design support apparatus 100 includes three graphical editing windows.
The setting chart display unit 114 displays a screen for performing setting for each time and confirming result information for each time. Further, the transport dialog display unit 115 displays a screen for controlling execution, pause, continuation, and termination of calculation.

FIG. 2 is a diagram showing a graphical editing window displayed by the two-dimensional display unit 111.
The graphical editing window displayed by the two-dimensional display unit 111 is referred to as an on-board device arrangement model editing screen. The two-dimensional display unit 111 displays a development view in which the satellite structure panel 1 included in the artificial satellite model is developed in a two-dimensional coordinate system, and a two-dimensional projection view of the mounting surface of the mounted device 2 arranged on each panel.
The model editing unit 120 displays the 2D of the mounted device 2 in the same manner as the graphic editing function mounted in commercially available word processor software or spreadsheet software on the mounted device arrangement model editing screen displayed by the 2D display unit 111. Projection views can be added, copied, deleted, moved, resized, and edited by cutting and pasting and dragging and dropping using mouse operations and keyboard input. Note that the characteristics include mass characteristics such as the density (density, surface density) of the shape model, mass point mass to be added, and added position in the satellite structure panel and each mounted device. For example, the model editing unit 120 can move the mounted device from one panel to another panel by drag and drop, as indicated by the broken line portion 4. The result edited on the on-board device arrangement model editing screen is reflected on the three-dimensional artificial satellite model on the three-dimensional satellite model editing screen displayed by the three-dimensional display unit 112 described later. The model editing unit 120 can also arrange the heat pipe 3 on the on-board device arrangement model editing screen, and define the heat conduction coupling between the on-board devices 2 by connecting the on-board devices 2 with the heat pipe 3. be able to. In addition, the two-dimensional display unit 111 can display the temperature calculation result calculated by the result calculation unit 140 (to be described later) on the on-board device arrangement model editing screen using a color corresponding to the temperature of each on-board device.

FIG. 3 is a diagram showing a graphical editing window displayed by the three-dimensional display unit 112. FIG. 4 is a diagram showing a display example in which a visual field range 31 of a mounted device that simulates a sensor or antenna mounted on an artificial satellite model, and an operation coverage surface 32 of a solar battery paddle or an antenna are model-displayed.
The graphical editing window displayed by the three-dimensional display unit 112 is called a three-dimensional satellite model editing screen. The three-dimensional display unit 112 displays the entire artificial satellite model including the on-board equipment as the three-dimensional model. The three-dimensional display unit 112 can display a satellite structure panel included in the artificial satellite model in a translucent or line drawing. Therefore, it is possible to see through the internal device placement state, and whether there is interference in the space occupied by the devices mounted on the result of editing on the two-dimensional device placement model editing screen displayed by the two-dimensional display unit 111. Etc. can be confirmed.
In addition, as shown in FIG. 4, when a predetermined operation such as button pressing is performed by the input device, the three-dimensional display unit 112, a visual field range 31 of a mounted device that simulates a sensor or an antenna, a solar cell paddle or an antenna The operation coverage surface 32 can be automatically displayed as a model. The operation coverage surface 32 is also referred to as an envelope. In FIG. 4, the three-dimensional display unit 112 displays the field of view range 31 from the sensor 34, and covers the surface when the artificial satellite mounted device indicated by the artificial satellite model is operated by the actuator, that is, the solar cell paddle 33 and the antenna. The outer peripheral surface (operating range) of the space swept when rotating or reciprocating is displayed as the operation coverage surface 32. The model editing unit 120 calculates the coverage surface from the size and arrangement of the onboard equipment set on the onboard equipment arrangement model editing screen or the 3D satellite model editing screen. Therefore, the user can design the on-board equipment arrangement while checking whether there is any interference with the sensor 34, the antenna, the solar battery paddle 33, or the like. Although the length of the visual field range 31 is actually very long or infinite length is correct, the purpose of the display is to confirm whether there is interference in the sensor visual field by the satellite structure itself or the mounted equipment. The display may be a finite length having an appropriate length as shown in FIG. In FIG. 4, although it is represented by a conical shape, it may naturally have other shapes such as a quadrangular pyramid depending on the type of sensor, and in the case of a sensor that performs sweeping by an actuator, the entire region swept by the visual field shape. You may display the outer peripheral surface.
The model editing unit 120 can also select, move, change the size, and edit the characteristics of the mounted device from the 3D satellite model editing screen displayed by the 3D display unit 112. The result edited on the 3D satellite model editing screen is reflected on the 2D satellite model on the on-board device arrangement model editing screen displayed by the 2D display unit 111. That is, the editing results of the on-board device arrangement model editing screen and the 3D satellite model editing screen are reflected mutually.
In addition, the three-dimensional display unit 112 can display the temperature calculation result calculated by the result calculation unit 140 (to be described later) on the three-dimensional satellite model editing screen with a color corresponding to the temperature of each mounted device.
The correspondence relationship between the mounted device on the mounted device arrangement model edit screen displayed by the 2D display unit 111 and the mounted device on the 3D satellite model edit screen displayed by the 3D display unit 112 is, for example, a color, hatching, or number. May be displayed on each screen. In addition, the name of the mounted device may be displayed on each screen. In addition, when the cursor is placed on the mounted device, the name of the mounted device may be displayed.

FIG. 5 is a diagram showing a mass characteristic display screen.
The two-dimensional display unit 111 and the three-dimensional display unit 112 display the mass characteristic display screen as an independent dialog when the model editing unit 120 performs a predetermined operation such as pressing a button.
On the mass characteristic display screen, the mass characteristic of the entire satellite model obtained by summing up the mass characteristics of each mounted device is displayed. On the mass characteristic display screen shown in FIG. 5, the mass, inertia tensor, and barycentric position are displayed as mass characteristics. By checking the mass characteristic display screen, the user can design the on-board equipment arrangement while taking into account the mass balance of the entire satellite.
In the above description, the mass characteristic display screen is displayed as an independent dialog, but may be displayed in a part of another window.

FIG. 6 is a diagram showing a graphical editing window displayed by the space model display unit 113.
The graphical editing window displayed by the space model display unit 113 is called a space model editing screen. The space model display unit 113 displays the shape, position, orbit, shadow region, and satellite shape, position, attitude, solar cell paddle shape, arrangement, and rotation of the celestial body as a three-dimensional model animation based on the definition of the user. . However, the display scale of the satellite can be set to a large value for the planet, and even if it is displayed so that the entire planet fits in the window, the satellite can be visually confirmed without affecting the analysis. Can be displayed. This screen has a corresponding input interface screen (not shown), which can add, delete, edit characteristics, and change the size and orientation of celestial bodies, satellites, and orbit models.

FIG. 7 is a diagram illustrating a screen displayed by the setting chart display unit 114.
A screen displayed by the setting chart display unit 114 is referred to as a time chart window. The setting chart display unit 114 includes a time chart arrangement area 61 and graph areas 62 and 63. The graph areas 62 and 63 include a power balance graph area 62 that displays a power balance, and a mounted device temperature graph area 63 that displays a mounted device temperature. In the time chart arrangement area 61 and the graph areas 62 and 63, the time elapses from left to right.
In the time chart arrangement area 61, the model editing unit 120 includes the directivity, maneuver (posture change), and onboard equipment of the satellite from the start time (satellite movement start time) to the end time (satellite movement end time). Power consumption, calorific value, directivity, rotation, and reciprocation of the equipment that operates with actuators such as solar cell paddles and antennas at each time step after the start time (every time elapsed from the start time) Each is defined (set) individually. Here, for example, a plurality of power consumption modes in which power consumption is set are prepared in advance such as power consumption mode 1 for power consumption mode 1 and power consumption mode 2 for power consumption mode 2. May be assigned to set the power consumption. Thereby, the power consumption can be easily set. Similarly, a plurality of modes may be prepared in advance for other setting items such as the heat generation amount, and the heat generation amount may be set by assigning a mode for each time. In FIG. 7, as an example, the power consumption is initially set to MODE1 and then switched to MODE2 (a predetermined power consumption is set for MODE1 and MODE2). Similarly, the heat generation amount is initially set to MODE5 and then switched to MODE6.
When the result calculation unit 140 described later starts calculation, the setting chart display unit 114 moves the time display cursor 64 indicating the time currently being calculated to indicate the time currently being calculated. Further, the model editing unit 120 sets the maneuver execution of the artificial satellite, the power consumption value, and the like according to the definitions (definitions of the power consumption mode, the heat generation mode, the maneuver, etc.) arranged at the position indicated by the time display cursor 64. The result is input to the result calculation unit 140. Then, the model editing unit 120 similarly reflects the definition on the three-dimensional graphic display on the space model editing screen. In other words, the attitude change of the artificial satellite due to the execution of the maneuver is reflected in the three-dimensional graphic display on the space model editing screen.
The setting chart display unit 114 displays the calculation results (result information) of the mounted device temperature, the heat balance of the mounted device, or the power balance in the graph areas 62 and 63. The setting chart display unit 114 adds the calculation result of the time currently being calculated as a plot at the position of the time display cursor 64 in the graph. That is, in FIG. 7, the calculation result of the time is displayed side by side under the setting information for each time. Thereby, the user can easily compare the setting with the result. Furthermore, at this time, the state represented by the three-dimensional model animation on the space model editing screen displayed by the space model display unit 113 is the state of the time indicated by the time display cursor 64. Therefore, the user can immediately know the interrelationship between the position and orientation of the satellite, the relative relationship with the celestial body, the power consumption mode set in the chart, the heat generation mode, and the calculation result.
In addition, when the time display cursor 64 is moved even after the calculation is finished or the calculation is paused, the 3D model animation on the space model editing screen displayed by the space model display unit 113 displays the state (frame) at that time. To do. Therefore, it is possible to confirm not only the result of the time being calculated (the time calculated most recently) but also the geometric relationship between the satellite and the celestial body at the time when the result has already been calculated. It is. The temperature of each mounted device at this time is the color display of the mounted device displayed on the mounted device arrangement model editing screen displayed by the two-dimensional display unit 111 or the three-dimensional satellite model editing screen displayed by the three-dimensional display unit 112. You can also know by. In particular, on the on-board device arrangement model editing screen displayed by the two-dimensional display unit 111, it is possible to grasp the relationship between the placement of the on-board device and the temperature distribution of the on-board device for each structure panel at the same time. Therefore, it is convenient when printing and documenting.

FIG. 8 is a diagram showing a transport dialog displayed by the transport dialog display unit 115.
The transport dialog includes a play button 71, a pause button 72, and a stop button 73. The model editing unit 120 can control execution, pause, continuation, and termination of calculations by operating these buttons with an input device.
During execution, the time for each calculation step is generated based on the expression “t _i = t _i−1 + Δt” obtained from the time Δt set in the time step 77. On-board equipment temperature and power balance are calculated based on this value. Here, t _i-1 is the time one step before. That is, the result calculation unit 140 calculates the temperature of the mounted device and the power balance every Δt time.
Each of the start time, the end time, and the time step has an input interface (input screen), and by setting these, the user sets the integration time step at the time of calculation and the start and end times of the calculation. be able to.
Note that multiple satellites can be placed at the same time to perform analysis simultaneously. The transport dialog is a modeless dialog, and other windows can be operated during display. Furthermore, in the above description, the calculation is performed sequentially for each time step, but it goes without saying that it can also be used as an interface for reproducing a result calculated once in advance.

Next, the trajectory calculation unit 130 will be described.
The trajectory calculation unit 130 performs trajectory calculation by the processing device. Orbital calculation requires astronomical object position calculation and satellite position calculation. As the position of the celestial body, a fixed position may be designated as necessary, or the time calendar of the position may be stored in a table in advance and read. As another means, the ephemeris that is publicly available by the Jet Propulsion Laboratory (JPL) of the National Aeronautics and Space Administration (NASA) can also be used. This method is a method in which coefficient sequence table data for representing astronomical positions in a Chebyshev polynomial is stored in a file in advance, and astronomical positions at arbitrary times are obtained by interpolation, and is well known as an accurate ephemeris. Yes. Of course, the user may arbitrarily select from these plural means. The position of the satellite is calculated based on orbital mechanics based on perturbation theory. A simple formula that takes into account only the secular term is known. For example, the North American Aerospace Defense Command (NORAD) has published a series of algorithms (SGP, SGP4, SDP4, SGP8, SDP8) based on standard general perturbation theory. They may be used. Alternatively, a trajectory that always circulates on the same trajectory without performing perturbation may be used according to the necessity of the purpose. Of course, a plurality of trajectory calculation methods may be prepared so that the user can arbitrarily select them.

  Next, each function of the result calculation unit 140 will be described. The result calculation unit 140, based on the setting information of the mounted device edited by the model editing unit 120 and the track information calculated by the track calculation unit 130, (1) temperature calculation of the mounted device, (2) power balance calculation, ( 3) Calculate mass characteristics. As described above, the result calculation unit 140 includes the temperature calculation unit 141, the power balance calculation unit 142, and the mass characteristic calculation unit 143 that perform the calculations (1), (2), and (3).

（Ｓ５：熱放射入力計算ステップ）
温度計算部１４１は、例えば、数１により求めた形態係数に基づき、数２から軌道における熱放射入力を計算する。

（Ｓ６）
数２による計算結果を利用して、温度計算部１４１は、軌道における熱入力を数３に従って数値積分により計算する。ここで、発熱量は、設定チャート表示部１１４が表示したタイムチャートウィンドウで設定した値である。

(1) Temperature calculation of mounted device The temperature calculation unit 141 calculates the temperature of the mounted device by the processing device. FIG. 9 is a flowchart showing a flow of temperature calculation of the mounted device.
(S1-S4: Form factor calculation step)
In order to calculate the temperature, it is first necessary to calculate the heat input from the parent body (Earth) to the surface of each structure panel, the reflection of sunlight, and the heat radiation from the sun. Therefore, first, the temperature calculation unit 141 calculates a view factor indicating how visible each other is between each structure panel surface and the sun or celestial body. For example, the temperature calculation unit 141 calculates the form factor by Equation 1. That is, for example, the temperature calculation unit 141 calculates the form factor when the parent body is viewed from each satellite structure panel included in the artificial satellite model by numerical integration using the information shown in FIG.

(S5: Thermal radiation input calculation step)
For example, the temperature calculation unit 141 calculates the thermal radiation input in the orbit from Equation 2 based on the form factor obtained by Equation 1.

(S6)
Using the calculation result according to Equation 2, the temperature calculation unit 141 calculates the heat input in the orbit by numerical integration according to Equation 3. Here, the heat generation amount is a value set in the time chart window displayed by the setting chart display unit 114.

(2) Power balance calculation The power balance calculation unit 142 calculates the power balance of the satellite using the processing device.
The power balance calculation unit 142 performs satellite power balance calculation according to Equation 4, for example. Here, the power consumption is a value set in the time chart window displayed by the setting chart display unit 114.

(3) Mass characteristic calculation The mass characteristic calculation unit 143 performs mass characteristic calculation of the satellite by the processing device. Here, the mass characteristic is an inertia tensor, a mass, and a barycentric coordinate composed of terms of inertia ratio and product of inertia. The mass characteristics of the entire satellite can be obtained by synthesizing all the components of the satellite including the structure and onboard equipment.
The mass characteristic calculation unit 143 performs mass characteristic calculation according to, for example, Equations 5 and 6. The mass of the element is calculated from, for example, surface area × surface density.

As described above, the display unit 110 displays the result (result information) calculated by the result calculation unit 140 on the display device. Then, the user again designs (edits) the placement of the mounted device while confirming the result displayed on the display device by the display unit 110. That is, the user uses the satellite design support apparatus 100 to repeatedly edit and calculate the arrangement of the on-board equipment. That is, the satellite design support apparatus 100 is an interactive graphical tool for designing the on-board equipment arrangement. At this time, the following effects can be obtained by designing the arrangement of the on-board equipment using the satellite design support apparatus 100.
According to the satellite design support apparatus 100, in the layout design of the on-board equipment, the user sets the on-board panel and layout of each equipment, the effective area (heat radiation area), the heating amount by the heater, and the temperature of each on-board equipment depends on the operation of the satellite. It can be confirmed by looking at the graph of the time chart window and the color display of the mounted device that the temperature does not deviate from the allowable temperature range while moving on the orbit throughout the period. If the temperature exceeds the allowable temperature range, a warning can be given by displaying in a predetermined color or blinking.
Further, according to the satellite design support device 100, in the layout design of the on-board equipment, the user sets the rated generated power of the solar cell paddle, the battery capacity, the power consumption of the on-board equipment, etc., and the discharge depth (DOD) of the battery is It can be confirmed by looking at the graph in the time chart window that the upper limit is not exceeded during the operation period of the satellite.
Furthermore, according to the satellite design support apparatus 100, in the layout design of the on-board equipment, the user sets the shape and the mass characteristics of the on-board equipment and each on-board equipment, and the deviation amount, mass, and inertia ratio from the reference point of the center of gravity coordinates are allowed. It can be confirmed by looking at the mass display that there is no deviation from the range.
That is, according to the satellite design support apparatus 100, the temperature change of each mounted device of the satellite moving in the orbit is calculated, and the influence of the mounted device arrangement on the structure panel surface with respect to the calculation result changes with time. Can be grasped intuitively in relation to the geometrical relative relationship with the position, posture, and celestial position.

The above is summarized as follows.
The satellite design support apparatus 100 includes the position of the celestial body, the radiation intensity or albedo (sunlight reflectivity), the shape, size, and attitude of the satellite structure constituted by a plurality of planes, and the shape, size, and heat of the mounted equipment. A model editing unit 120 that can define and edit balance characteristics;
A development view of the satellite structure model is automatically arranged and displayed on a two-dimensional coordinate system, and on-panel equipment arranged on each panel is projected and displayed on the panel, thereby providing a three-dimensional equipment arrangement and shape. A display unit 110 (two-dimensional display unit 111) that can be edited by cutting and pasting on a two-dimensional development panel;
An orbit calculation unit 130 for calculating a satellite position at an arbitrary time based on orbital mechanics;
Based on the relative geometric relationship between the satellite position calculation result and the attitude of the satellite, the position of the mother body in the satellite orbit, and the shadow area of the sunlight cast by the mother body, the infrared radiation intensity, albedo, and solar radiation of the mother body A function for calculating the amount of heat incident on each satellite structure panel surface by means of, and a function for calculating the temperature of each mounted device based on the calculation result of the amount of incident heat and the heat balance characteristics of the mounted device and the mounted device. A result calculation unit 140 (temperature calculation unit 141) having
A display unit 110 (space model display unit 113) that displays a three-dimensional animation of the celestial body and the range of sunlight shadows cast by the celestial body, and a satellite;
It has the display part 110 (2D display part 111, 3D display part 112, setting chart display part 114) which displays the calculation result of the said mounted apparatus temperature visually.

In addition, the model editing unit 120 can define and edit the power balance and rotation of each installed device including the solar battery paddle,
The result calculation unit 140 calculates the amount of sunlight incident on the surface of the solar cell based on the satellite position calculation result and the relative geometric relationship between the attitude of the satellite, the celestial position, and the shadow area of the sunlight cast by the celestial body. In addition, the power balance calculation calculates the power balance of the entire satellite based on the calculation result of the incident amount of sunlight and the power balance of each on-board device including the arrangement, rotation, shape, size, and solar paddle of the solar cell surface. Part 142,
The display unit 110 (setting chart display unit 114) can visually display the calculation result of the power balance.

Furthermore, the model editing unit 120 (heat balance characteristic editing unit) can set the heat generation amount of each mounted device for each of a plurality of modes,
The model editing unit 120 (time chart editing unit) is based on the display of the display unit 110 (setting chart display unit 114), and can be used in any one or more time intervals within the calculation interval on the time axis of the on-board device temperature calculation. The calorific value mode can be selected,
When calculating the temperature of the mounted device, the result calculation unit 140 (temperature calculation unit 141) is characterized in that the heat generation amount specified in the heat generation amount mode is added to the heat input to the mounted device and used.

Furthermore, the model editing unit 120 (power balance characteristic editing unit) can set the power consumption of each mounted device for each of a plurality of modes,
The result calculation unit 140 (power balance calculation unit 142) calculates the total power consumption by totaling the power consumption of the mounted devices for each power consumption mode,
Based on the display of the display unit 110 (setting chart display unit 114), the model editing unit 120 (time chart editing unit) is arbitrarily and within one or more time intervals within the calculation interval on the time axis of the satellite power balance calculation. The power consumption mode can be selected,
The result calculation unit 140 (power balance calculation unit 142) uses the total power consumption specified in the power consumption mode when calculating the power balance of the satellite.

The display unit 110 (setting chart display unit 114)
While displaying the time chart to set the mode visually, the calculation result is output to the graph,
The time chart and the graph are displayed side by side with the time axis aligned, and have a time display cursor indicating a specific position on the time axis of the time chart and the graph, and a frame being displayed in a three-dimensional animation The position on the time axis coincides with the position on the time axis of the time display cursor.

Furthermore, the model editing unit 120 can define and edit the mass characteristics of each mounted device,
The result calculation unit 140 calculates the mass characteristics of at least one or more items of the entire satellite based on the on-board equipment arrangement and the mass characteristics of each on-board equipment, that is, the inertia performance factor, inertial product, mass, and barycentric coordinates around each axis.
The result calculation unit 140 displays at least one item of mass characteristics of the entire satellite.

Furthermore, the model editing unit 120 can automatically create an operation coverage surface when the mounted device is operated by an actuator,
The display unit 110 (three-dimensional display unit 112) is characterized in that the generated coverage model can be superimposed and displayed on the satellite model together with the mounted device.

Further, the visual field range from the display unit 110 (three-dimensional display unit 112) mounted device can be superimposed and displayed on the satellite model together with the mounted device.

That is, according to the satellite design support apparatus 100, a CAD apparatus and software that reduce the time and skill necessary to design the onboard equipment arrangement of the onboard equipment are provided.
That is, the satellite design support apparatus 100 automatically deploys and arranges each panel of the three-dimensional satellite structure model on the two-dimensional coordinate system, and projects and displays the mounted devices arranged on each panel on the panel. It has a 2D model editing interface that allows you to edit the layout and shape of 3D on-board equipment by cutting and pasting on a 2D development panel. Furthermore, the satellite design support apparatus 100 can also execute satellite position calculation in orbit based on orbital dynamics, based on radiation of the parent body, albedo (reflection), and the amount of heat incident from time to time on each structure panel surface by the sun. In addition, it has a function of calculating the heat balance and temperature of the mounted device with respect to the mounted device arrangement and the characteristics of the mounted device set by the user. The position and orientation of celestial bodies and satellites, changes in the shadow area of sunlight due to celestial bodies, and the state of rotation of the solar battery paddle are displayed in 3D graphics, and the calculation results of the temperature of the onboard equipment are displayed simultaneously in graphs, so the user sometimes It is possible to easily confirm the layout design of the on-board equipment while intuitively grasping the relationship between the position of the structure panel surface that changes every moment, the range of the shadow of the sun and the celestial body, and the on-board equipment temperature.

Next, the hardware configuration of the satellite design support apparatus 100 in the embodiment will be described.
FIG. 11 is a diagram illustrating an example of a hardware configuration of the satellite design support apparatus 100.
As shown in FIG. 11, the satellite design support apparatus 100 includes a CPU 911 (also referred to as a central processing unit, a central processing unit, a processing unit, an arithmetic unit, a microprocessor, a microcomputer, and a processor) that executes a program. . The CPU 911 is connected to the ROM 913, the RAM 914, the LCD 901 (Liquid Crystal Display), the keyboard 902, the mouse 903, the communication board 915, and the magnetic disk device 920 via the bus 912, and controls these hardware devices. Instead of the magnetic disk device 920, a storage device such as an optical disk device or a memory card read / write device may be used.

  The ROM 913 and the magnetic disk device 920 are examples of a nonvolatile memory. The RAM 914 is an example of a volatile memory.

  An operating system 921 (OS), a window system 922, a program group 923, and a file group 924 are stored in the magnetic disk device 920 or the ROM 913. The programs in the program group 923 are executed by the CPU 911, the operating system 921, and the window system 922.

The program group 923 includes software and programs that execute the functions described as “display unit 110”, “model editing unit 120”, “trajectory calculation unit 130”, “result calculation unit 140”, and the like in the above description. The program is stored. The program is read and executed by the CPU 911.
In the file group 924, information, data, signal values, variable values, and parameters such as “equipment temperature”, “power balance”, “mass characteristics”, etc. in the above description are stored in the “file” and “database” items. Is remembered as The “file” and “database” are stored in a recording medium such as a disk or a memory. Information, data, signal values, variable values, and parameters stored in a storage medium such as a disk or memory are read out to the main memory or cache memory by the CPU 911 via a read / write circuit, and extracted, searched, referenced, compared, and calculated. Used for the operation of the CPU 911 such as calculation / processing / output / printing / display. Information, data, signal values, variable values, and parameters are temporarily stored in the main memory, cache memory, and buffer memory during the operation of the CPU 911 for extraction, search, reference, comparison, calculation, calculation, processing, output, printing, and display. Is remembered.
In addition, the arrows in the flowcharts in the above description mainly indicate input / output of data and signals, and the data and signal values are recorded in a memory of the RAM 914 and other recording media such as an optical disk. Data and signals are transmitted online via a bus 912, signal lines, cables, or other transmission media.

  In addition, what is described as “to part” in the above description may be “to circuit”, “to device”, “to device”, “to means”, and “to function”. It may be “step”, “˜procedure”, “˜processing”. In addition, what is described as “˜device” may be “˜circuit”, “˜device”, “˜equipment”, “˜means”, “˜function”, and “˜step”, “ ~ Procedure "," ~ process ". Furthermore, what is described as “to process” may be “to step”. That is, what is described as “˜unit” may be realized by firmware stored in the ROM 913. Alternatively, only software, hardware such as elements, devices, substrates, and wiring, a combination of software and hardware, or a combination of firmware may be used. Firmware and software are stored in a recording medium such as ROM 913 as a program. The program is read by the CPU 911 and executed by the CPU 911. That is, the program causes a computer or the like to function as the “˜unit” described above. Alternatively, the computer or the like is caused to execute the procedures and methods of “to part” described above.

  That is, the satellite design support apparatus 100 may be read as a satellite design support program and a satellite design support method. In the case of the satellite design support program, the “˜unit” included in the satellite design support apparatus 100 is read as “˜processing”, and in the case of the satellite design support method, the “˜unit” included in the satellite design support apparatus 100. May be read as "~ step".

3 is a functional block diagram showing functions of the satellite design support apparatus 100. FIG. The figure which shows an example of the screen structure and usage condition of an on-board equipment arrangement model edit screen. The figure which shows an example of the screen structure and usage condition of a three-dimensional satellite model edit screen. The figure which shows an example of the display condition on the three-dimensional satellite model edit screen of the visual field of an mounted apparatus, and an operation | movement coverage surface. The figure which shows an example of the display screen of a mass characteristic calculation result. The figure which shows an example of a screen structure and usage condition of a space model edit screen. The figure which shows an example of the screen structure and usage condition of a time chart window. The figure which shows an example of a screen structure and usage condition of a transport dialog. The figure which shows the calculation flow of onboard equipment temperature. The supplementary explanatory drawing of the formula of a form factor. The figure which shows an example of the hardware constitutions of the satellite design assistance apparatus.

Explanation of symbols

  1 Satellite structure panel, 2 Onboard equipment, 3 Heat pipe, 31 Field of view, 32 Operating coverage surface, 33 Solar cell paddle, 34 Sensor, 51 Mother body, 52 Satellite, 53 Satellite orbit, 54 Mother body shadow area, 61 time Chart layout area, 62 Power balance graph area, 63 On-board equipment temperature graph area, 64 Time display cursor, 65 Edit mode display area, 71 Play button, 72 Pause button, 73 Stop button, 74 Calculation start time setting interface, 75 Calculation End time setting interface, 76 Time display / setting interface, 77 Time step setting interface, 91 Structure panel surface, 92 Sun, 93 Mother body surface, 100 Satellite design support device, 110 Display unit, 111 2D display unit, 112 3D Display unit, 11 Space model display section, 114 setting chart display section, 115 transport dialog display section, 120 model editing section, 130 orbit calculation section, 140 result calculation section, 141 temperature calculation section, 142 power balance calculation section, 143 mass property calculation section, 150 Result display section.

Claims (23)

It is a satellite design support device that supports the layout design of onboard equipment for artificial satellite
A two-dimensional display unit that displays on a display device a development view in which a satellite model in which the on-board equipment is arranged is developed in a two-dimensional coordinate system;
A model editing unit that edits setting information of at least one of an arrangement, a shape, and a size of the mounted device of the artificial satellite model by operating a development view displayed by the two-dimensional display unit via an input device;
Based on the setting information of the device equipped with the satellite model edited by the model editing unit, the amount of heat incident on the satellite model when the satellite indicated by the satellite model moves in a predetermined orbit is calculated. A temperature calculation unit for calculating a temperature of the mounted device of the artificial satellite model at a predetermined time after the start of movement in the predetermined orbit by a processing device;
A satellite design support apparatus, comprising: a result display unit configured to display, on the display device, the temperature of the device mounted on the artificial satellite model calculated by the temperature calculation unit as result information. The model editing unit sets the calorific value of the on-board equipment at each time after the artificial satellite starts moving,
2. The temperature calculation unit calculates a temperature of a device mounted on the artificial satellite model at the predetermined position based on an amount of heat incident on the artificial satellite model and the calorific value. The satellite design support apparatus described. The model editing unit edits the setting information of the onboard device including the solar battery paddle, and sets the power balance of the onboard device,
The satellite design support device further includes:
Based on the power balance of the on-board equipment set by the model editing unit, a power balance calculation for calculating a power balance of the artificial satellite model at a predetermined position when the artificial satellite moves in the predetermined orbit by a processing device Part
The satellite design support apparatus according to claim 1, wherein the result display unit displays the power balance calculated by the power balance calculation unit as result information. The model editing unit sets the power consumption of the mounted device at each time after the start of movement of the artificial satellite,
The power balance calculation unit calculates a power balance of the artificial satellite model at the predetermined position based on a power balance of the mounted device and power consumption set by the model editing unit. Item 4. The satellite design support device according to item 3. The satellite design support device further includes:
A setting chart display unit for displaying a time chart for setting at least one of the heat generation amount and power consumption of the mounted device on a display device;
The model editing unit sets at least one of the heat generation amount and power consumption of the mounted device at each time after the start of movement of the artificial satellite by operating the time chart displayed by the setting chart display unit. And
5. The satellite design support apparatus according to claim 2, wherein the result display unit displays the result information as a graph side by side or overlaid with the time chart displayed by the setting chart display unit. The result display unit displays a three-dimensional animation of the artificial satellite moving in the predetermined orbit and the result information at a predetermined time after the artificial satellite starts moving in the predetermined orbit indicated by the three-dimensional animation. The satellite design support apparatus according to claim 1, wherein 7. The result display unit displays the artificial satellite moving in the predetermined orbit so that a portion of the artificial satellite that is exposed to sunlight and a portion that is not irradiated can be identified. The satellite design support device described in 1. When displaying the result information as a graph, the result display unit indicates the result information at a predetermined time after the start of movement of the artificial satellite in the predetermined orbit indicated by the three-dimensional animation in the graph. The satellite design support device according to claim 6 or 7, wherein the portion is highlighted and displayed. The model editing unit sets mass characteristics including at least one of a mass of mass points to be added, an addition position, a density, and an area density for the mounted device,
The satellite design support device further includes:
Based on the shape and size of the on-board equipment and the mass characteristics set by the model editing unit, the mass characteristics including at least one of inertia ratio, inertial product, mass, and barycentric coordinates of the satellite model A mass characteristic calculation unit for calculating
9. The satellite design support apparatus according to claim 1, wherein the result display unit displays a mass characteristic of the artificial satellite model calculated by the mass characteristic calculation unit. The satellite design support device further includes:
The satellite model on which the mounted device displayed by the two-dimensional display unit is arranged is displayed three-dimensionally, and the operating coverage surface of the mounted device operated by the actuator of the artificial satellite indicated by the artificial satellite model is displayed on the display device. The satellite design support apparatus according to claim 1, further comprising a three-dimensional display unit. The satellite design support apparatus according to claim 10, wherein the three-dimensional display unit displays a field-of-view range from a mounted device on an artificial satellite model together with the mounted device. It is a satellite design support program that supports the placement design of onboard equipment for artificial satellites,
A two-dimensional display process for displaying a development view in which a satellite model in which an on-board device is arranged is developed in a two-dimensional coordinate system;
A model editing process for editing setting information of at least one of the arrangement, shape, and size of the mounted device of the artificial satellite model by manipulating the developed view displayed in the two-dimensional display process;
The amount of heat incident on the satellite model when the artificial satellite indicated by the artificial satellite model moves in a predetermined orbit is calculated based on the setting information of the onboard device of the artificial satellite model edited by the model editing process. A temperature calculation process for calculating a temperature of the mounted device of the artificial satellite model at a predetermined time after the start of movement in the predetermined orbit,
A satellite design support program for causing a computer to execute a result display process for displaying the temperature of the artificial satellite model calculated by the temperature calculation process as result information. In the model editing process, for each time after the start of movement of the artificial satellite, set the heat generation amount of the onboard equipment,
The temperature calculation process calculates the temperature of the device mounted on the artificial satellite model at the predetermined position based on the amount of heat incident on the artificial satellite model and the calorific value. The satellite design support program described. In the model editing process, the setting information of the mounted device including the solar battery paddle is edited, and the power balance of the mounted device is set,
The satellite design support program further includes:
Based on the power balance of the on-board equipment set in the model editing process, a power balance calculation for calculating the power balance of the artificial satellite model at a predetermined position when the artificial satellite moves in the predetermined orbit by a processing device Let the computer execute the process,
14. The satellite design support program according to claim 12, wherein the result display process displays the power balance calculated in the power balance calculation process as result information. In the model editing process, for each time after the start of movement of the artificial satellite, set the power consumption of the on-board equipment,
The power balance calculation process calculates a power balance of the satellite model at the predetermined position based on a power balance of the mounted device and power consumption set by the model editing process. Item 15. A satellite design support program according to Item 14. The satellite design support program further includes:
Causing the computer to execute a setting chart display process for displaying a time chart for setting at least one of the heat generation amount and power consumption of the mounted device;
In the model editing process, by operating the time chart displayed in the setting chart display process, at least one of the heat generation amount and power consumption of the mounted device is set for each time after the artificial satellite starts moving. And
16. The satellite design support program according to claim 13, wherein in the result display process, the result information is displayed as a graph side by side or overlaid with the time chart displayed in the setting chart display process. In the result display process, the three-dimensional animation of the artificial satellite moving in the predetermined orbit and the result information at a predetermined time after the artificial satellite starts moving in the predetermined orbit indicated by the three-dimensional animation are displayed. The satellite design support program according to any one of claims 12 to 16, wherein the program is a satellite design support program. 18. In the result display processing, together with the artificial satellite moving in the predetermined orbit, a portion of the artificial satellite that is exposed to sunlight and a portion that is not irradiated are displayed so as to be distinguishable. Satellite design support program described in 1. In the result display process, when the result information is displayed as a graph, the result information at a predetermined time after the start of movement of the artificial satellite in the predetermined orbit indicated by the three-dimensional animation is displayed. The satellite design support program according to claim 17 or 18, wherein the portion is highlighted and displayed. In the model editing process, a mass characteristic including at least one of the mass of the mass point to be added, the addition position, the density, and the surface density is set for the mounted device,
The satellite design support program further includes:
Based on the shape and size of the on-board equipment and the mass characteristics set in the model editing process, the mass characteristics including at least one of inertia ratio, inertial product, mass, and barycentric coordinates of the satellite model The computer executes mass characteristic calculation processing for calculating
The satellite design support program according to any one of claims 12 to 19, wherein in the result display process, the mass characteristic of the artificial satellite model calculated in the mass characteristic calculation process is displayed. The satellite design support program further includes:
The artificial satellite model in which the on-board equipment to be displayed in the two-dimensional display processing is arranged is three-dimensionally displayed, and the operation coverage surface of the on-board equipment operated by the artificial satellite actuator indicated by the artificial satellite model is displayed on the display device. The satellite design support program according to any one of claims 12 to 20, wherein the computer executes a three-dimensional display process. The satellite design support program according to claim 21, wherein, in the three-dimensional display process, a field-of-view range from the mounted device is displayed on an artificial satellite model together with the mounted device. It is a satellite design support method that supports the placement design of onboard equipment for artificial satellites,
A two-dimensional display step in which the display device displays a development view in which the satellite model in which the on-board equipment is arranged is developed in a two-dimensional coordinate system;
A model editing step in which the input device edits the setting information of at least one of the arrangement, shape, and size of the device on which the artificial satellite model is mounted by operating the development view displayed in the two-dimensional display step;
The processor enters the artificial satellite model when the artificial satellite indicated by the artificial satellite model moves in a predetermined orbit based on the setting information of the equipment equipped with the artificial satellite model edited in the model editing step. A temperature calculation step of calculating an amount, and calculating a temperature of a mounted device of the artificial satellite model at a predetermined time after the start of movement in the predetermined orbit,
A satellite design support method, comprising: a result display step in which the display device displays the temperature of the artificial satellite model calculated in the temperature calculation step as result information.

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