JP2001116584A - Time-correcting apparatus to be loaded to artificial satellite and command apparatus - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain a time-correcting apparatus to be loaded to an artificial satellite which corrects an error generated to an actually observed position in accordance with an error caused by the perturbation of an orbit between an estimated orbit value and the actual orbit position. SOLUTION: A pass time of an orbit position which is a time reference of a satellite orbit, e.g. an ascending node or the like can be updated to a newest value with the use of a satellite position/time-determining part using a GPS(Global Positioning System) receiver or the like. Moreover, a time change generated to the pass time of the orbit position by the perturbation of the orbit is made a correction amount for a satellite-loaded clock.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

TECHNICAL FIELD The present invention relates to, for example,
The present invention relates to a time correction device of an observation device mounted on an earth observation satellite for observing the sea surface, the atmosphere, weather, and the like, and a command issuing device.

[0002]

2. Description of the Related Art Generally, the observation position of an earth observation satellite is:
Based on the observation request position, a plan is created based on the satellite position estimated by the propagation model on the ground. This plan is managed by the ascending intersection passing time in each round. The ascending intersection passage time, which is a reference for this observation time management, is determined by measuring the satellite orbital position from the ground, propagating the orbit, and transmitting it to the satellite as command data expressed by the clock time of the satellite.

[0003] The observation device mounted on the artificial satellite is
Observation plans such as observation start and observation end were given based on the elapsed time from the ascending intersection passing time. After storing the observation plan command in the memory of the command issuing device, the observation plan command is issued at the planned time attached to the command data by sequentially referring to the time data of the satellite clock. Hereinafter, such a command related to the planned operation is simply referred to as a command or a stored command.

[0004]

After setting the observation plan, the orbital motion of the artificial satellite, especially the in-orbital motion, is perturbed by disturbance fluctuations which are ignored or unpredictable by the propagation model. Conventional earth observation satellites or the observation devices mounted on them are configured as described above, and actual observations are made according to the error between the orbit predicted value caused by this orbit perturbation and the actual orbit position. There is an error in the target position. In an observation sensor in which the observation width of the observation sensor can be relatively large, this observation position error is dealt with by making the observation width of the sensor absorbable. However, with a high-resolution sensor or the like, the observation width is relatively narrow, so this is difficult, and the observation point leaks. For example, if the predicted value of the atmospheric density is underestimated, the actual altitude descent rate of the satellite increases, and an error occurs in which the orbital period is shortened. Therefore, an observation point error occurs in the orbit plane.

This will be described with reference to FIG. In FIG. 9, 1 is the earth viewed from the inward direction of the equator, 2 is the orbit of the satellite, 3 is the equatorial plane, 4 is the orbital position of the satellite at the ascending intersection, 5 is an ideal with no orbital perturbation from the time of the observation plan Orbital position, 6 is the actual orbital position with orbital perturbation, similarly, 7 is the ideal observational orbital position without orbital perturbation from the time of the observation plan, and 8 is the The actual observed orbital position with orbital perturbation. As described above, if there is a perturbation in the orbit, if the observation operation is managed based on the elapsed time from the ascending intersection, there is a problem that the observation position is greatly shifted from the time of planning.

[0006] Even if there is a trajectory error that could not be predicted at the time of the terrestrial imaging plan, the imaging range in the trajectory advancing direction should be expanded including an error margin in order to reliably capture the observation scheduled point. That is, it is necessary to increase the observation time. As a result of the increase in the amount of observation data, there has been a problem that the capacity of a data recorder mounted on a satellite increases, the capacity of a data line to the ground increases, and further, the post-processing of observation data in terrestrial processing increases.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-described problem. After an observation plan is set, the propagation model receives an external disturbance that is ignored or unpredictable by a propagation model, and the orbital motion of an artificial satellite, particularly, the in-orbital motion. Is perturbed, and an artificial satellite equipped with a satellite that can correct the actual observation position error caused by the error between the orbit predicted value caused by this orbit perturbation and the actual orbit position in an artificial satellite whose observation plan is managed by time information A time correction device and a command device are provided.

[0008]

The satellite time correction apparatus according to the first and second aspects of the present invention is, for example, a GPS (Global Positioning).
System) By using a satellite position determination unit using a receiver,
For example, it is possible to update the passing time of the orbital position based on the time of the satellite orbit such as an ascending intersection to the latest value, and the time change occurring at a certain orbital position passing time due to orbital perturbation is corrected with the correction amount of the satellite mounted clock. It is intended to be.

The artificial satellite command device according to the third and fourth aspects of the present invention predicts the artificial satellite orbital position error after the operation plan is created, converts the error into a time error and uses it as a time correction amount, and performs the artificial satellite operation. The scheduled execution times of these stored commands are rewritten so that the stored commands are executed at the orbital positions assumed when the operation plan was created.

The satellite command device according to the fifth and sixth aspects of the present invention predicts the satellite orbital position error after the operation plan is created, converts the error into a time error, and uses it as a time correction amount to perform the satellite operation. The stored command execution time is corrected by adding a time correction amount to the reference time at which the stored command is read so that the stored command is executed at the orbital position assumed when the operation plan is created. .

A satellite command device according to a seventh aspect of the present invention predicts a satellite orbital position error after an operation plan is created,
This is converted into a time error to be a time correction amount, and the scheduled execution time of these stored commands is rewritten so that the stored command for performing the satellite operation is executed at the orbital position assumed at the time of creating the operation plan. A device that receives the corrected time amount can obtain the corrected time amount.

The satellite command device according to an eighth aspect of the present invention predicts a satellite orbital position error after the operation plan is created,
This is converted into a time error to be a time correction amount, and the time correction amount is set at a reference time at which these stored commands are read so that the stored command for operating the satellite is executed at the orbital position assumed at the time of creating the operation plan. In addition, the time of execution of the stored command is corrected, and a device that receives the stored command can obtain the corrected time amount.

[0013]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a block diagram showing Embodiment 1 of the present invention. 101 is a data table that stores the expected orbital position at the time of the observation plan and the scheduled time at which the satellite is located at the planned orbital position, 102 is the orbital position determination unit equipped with the satellite, 103 is the clock unit equipped with the satellite, 104 is Predicted orbital position at the time of the observation plan and its predicted time 101
Comparing section with the actual orbit position and its time, 105
Is a correction unit for adding the correction time amount of the comparison unit 104 to the time output of the clock unit 103.

FIG. 2 is a diagram showing an example of data stored in the data table 101. As shown in FIG. Here, a polar orbit observation satellite is taken as an example, and the predicted orbit position at the time of the observation plan is given by the number of orbits and the latitude argument in each orbit.

Next, the operation will be described. Generally, the observation position of the earth observation satellite is based on the observation request position,
A plan is created based on the satellite positions estimated by the terrestrial propagation model. This plan is managed, for example, by the ascending intersection passing time in each round. The expected time of passage through the ascending intersection, which is the basis for this observation time management, is determined by measuring the satellite orbital position from the ground,
Determined by orbit propagation. The data table 101 is obtained by converting the predicted orbit position of the orbit and the predicted time to be the orbit position into data at certain intervals. 106 is the expected latitude argument corresponding to the expected orbital position at the time of the observation plan, 107
Is the expected time at that latitude argument,
And 107 are described in the data table 101 as a pair.

On the other hand, the actual orbit of the satellite is different from the predicted value due to a disturbance not included in the prediction. The result of measurement of the orbital position in the actual flight by the orbital position determination unit 102 is 108. The time data at that time is the output 109 of the clock unit 103. Orbital perturbations are larger in the orbital plane than in the orbital plane and are the main causes of errors in earth observation. Therefore, as shown in FIG. 2, for example, it is possible to make a table of the predicted values of the trajectory by the latitude argument and the time, and to compare the predicted values with the actual values. Here, the clock unit 103 outputs a time counted from the ascending intersection passing time as an example. Therefore, this time value is cleared to 0 seconds every time the vehicle passes the ascending intersection. For example,
In the satellite, the orbital position determination unit 102 outputs the measured value 108 of the latitude argument at certain time intervals. The clock unit 103 has a time value
Outputs 109.

The comparison unit 104 receives the output 108 of the orbital position determination unit and the time value 109, and searches the predicted latitude argument 106 stored in the data table 101 using the measured value 108 of the latitude argument as the search latitude argument value 122. This search uses the search latitude argument value 1
It is checked whether there is an expected latitude argument 106 that matches 22 or an expected latitude argument value 106 whose search latitude argument value 122 exceeds that value for the first time since the previous search. Applicable expected latitude argument value 1
If there is 06, the predicted latitude argument value 106 and the predicted time value 107 corresponding to the predicted latitude argument value 106 are read, and the time correction amount 110 is calculated. The time correction amount 110 can be calculated by the following equation, for example.

ΔT = Tp−Tr + (θr−θp) / ω (1)

Here, ΔT is a time correction amount 110, θp is a latitude argument 106 set in the data table 101, Tp is an estimated time 107 located at the latitude argument, θr is a measured value 108 of the actual latitude argument, Tr is the time 109 when the measured value is measured. Ω is the orbital angular velocity value, and may be an expected value thereof. Note that even if there is a processing time delay in the orbital position determination unit 102, since this processing time delay is substantially constant, the processing time delay may be subtracted from the time value 109 of the clock unit 103.

The concept of time correction will be described with reference to FIG.
The expected time is an estimated time calculated from the ascending intersection passing time in each round. 5 is the satellite position with a latitude argument of 90 degrees when there is no orbital perturbation from the time of the observation plan, and the estimated time is 1500
Seconds. Reference numeral 6 denotes a satellite position 1500 seconds after the ascending intersection passing time in the case of an actual orbit having an orbital perturbation with respect to 5, and in this example, since the orbital perturbation in which the altitude decreases, the ground speed becomes The speed is increased compared to the orbit without perturbation, and the latitude argument is over 90 degrees. It is assumed that the time at which the perturbation passed the latitude argument of 90 degrees in a certain orbit (the time calculated from the ascending intersection passing time) was 1495 seconds. By the above-described operation, the time difference of 5 seconds is calculated as the time correction amount. 7 is the ideal orbital position of 135 degrees latitude argument without orbital perturbation from the time of the observation plan.
Seconds are assumed times. 8 is 2250 with orbital perturbation
This is the satellite position after a second. Observation here causes an observation position error. On the other hand, the time is corrected using the time correction amount of 5 seconds, and the observation command issuance is advanced by 5 seconds and executed.
It can be observed at position 10 at 5 degrees.

If this calculation is performed at several points around the orbit or at least once before the observation, the time lag from the planning time with the latitude argument passing over the observation point can be predicted. The correction amount 110 is output. The correction unit 105
By adding the time correction amount 110 to the output of the clock section 103 mounted on the satellite, the corrected time value 11 adapted to the perturbed orbit is obtained.
1 can be output.

In FIG. 1, the orbital position determining unit 102
Although the clock unit 103 is shown as a separate element, these units may be used as the GPS receiving unit 112 as shown in FIG. Further, the clock unit 103 outputs the time calculated from the ascending intersection passing time as an example, but the elapsed time may be a plurality of rounds without being cleared when the ascending intersection passes.

As described above, according to the first embodiment, since the passage time of the orbital position of the satellite orbit, such as the ascending intersection, can be updated to the latest value, the orbit requiring time correction from this time reference can be updated. Since the distance to the position can be reduced, for example, to within one revolution, the orbit perturbation during this period can be made smaller than in the case of the related art.

Embodiment 2 FIG. FIG. 4 is a block diagram showing Embodiment 2 of the present invention. 101 is a data table for storing the predicted orbit position and the predicted time at the time of the observation plan, and 10
2 is an orbital position determining unit equipped with an artificial satellite, 103 is a clock unit equipped with an artificial satellite, 104 is a comparison unit that compares the expected orbital position 106 at the time of the observation plan and its expected time 107 with the actual orbital position and its time, Reference numeral 105 denotes a correction unit that adds the correction time amount 110 of the comparison unit 104 to the time output 109 of the clock unit 103.

Next, the operation of the second embodiment is the same as that of the first embodiment.
Only the search method of the data table 101 that is different from the operation described above will be described. The orbital position determination unit 102 outputs the measured value 108 of the latitude argument at certain time intervals. Clock section 1
03 outputs the time value 109. The comparison unit 104 receives the output 108 of the orbital position determination unit and the time value 109, and searches the expected time value 107 stored in the data table 101 using the time value 109 as the search time value 123. This search checks whether there is an expected time value 107 that matches the search time value 123 or an expected time value 107 whose search time value 123 exceeds that value for the first time since the previous search. If there is a corresponding expected time value 107, the predicted time value 107 and the corresponding predicted latitude argument 106 are read out, and the time correction amount 110 is calculated. As in the first embodiment, the time correction amount 110 can be calculated by, for example, the above equation (1). In FIG. 4, the orbital position determining unit 102 and the clock unit 103 are shown as separate elements, but these may be used as the GPS receiving unit 112 as in the first embodiment.

As described above, according to the second embodiment, the passing time of the orbital position of the satellite orbit, such as the ascending intersection, can be updated to the latest value. Since the distance to the position can be reduced, for example, to within one revolution, the orbit perturbation during this period can be made smaller than in the case of the related art.

Embodiment 3 FIG. 5 is a block diagram showing a third embodiment of the present invention. 113 is the planned time value data of the stored command written in the memory, 114 is the command data of the stored command, 115 is the clock unit 1 with the artificial satellite
A stored command reading unit that selects a stored command to be issued at each time according to the time value 109 of 03,
120 is the time correction amount 1 of the comparing unit 104
This is a memory correction unit that performs ten corrections.

Next, the operation will be described. The stored command is composed of planned time value data 113 and command data 114. For example, a stored command of the contents of the planned time (1234 seconds) and the contents of the command (observation device ON) are stored in the memory at address #N. By the operation described in the first or second embodiment of the present invention, comparison section 104 outputs time correction amount 110 for providing the same latitude argument between the time when the stored command was planned and the actual value. If this process is performed at several points around the orbit or before observation, it is possible to predict the time difference from the planning time with the latitude argument passing over the observation point,
The comparison unit 104 outputs the time correction amount 110 before the start of observation. When the time correction amount 110 is calculated, the planned time value data of the stored command written in the memory
113 is rewritten by the function of the memory correction unit 120.

On the other hand, the stored command reading section 115
Scans the value of the planned time value data 113 written in the memory at regular time intervals to find the planned time value data 113 that matches the time value 109. If there is the corresponding planned time value data 113, the command data 114 to be combined with the data is selected and issued. At this time, the planned time value data 113 of the stored command has already been updated by the time correction amount 110 in consideration of the orbital fluctuation, so that even if the issuance of the command is managed by the time information, there is not much difference from the planned time. A stored command can be issued at the orbital position of the latitude argument. The orbital position determining unit 102 and the clock unit 103
Are represented as separate elements, but they may be constituted by a GPS receiving unit.

As described above, according to the third embodiment, it is possible to predict the orbital position error of the artificial satellite after the operation plan is created, and to convert this into a time error to calculate the corrected time amount. Therefore, if an observation plan is given by the latitude argument of each orbit, the elapsed time from the ascending intersection passing time can be measured.
Further, by measuring the orbital position and its time during the subsequent orbit, the amount of change in orbital orbiting time due to orbital perturbation can be predicted. By using the prediction result to calculate the time correction amount and correcting the scheduled execution time of the stored command, the observation position error due to the orbit perturbation can be reduced.

Embodiment 4 FIG. FIG. 6 is a block diagram showing Embodiment 4 of the present invention. Reference numeral 113 denotes planned time value data of the stored command, and reference numeral 114 denotes command data of the stored command, which are stored in the memory as in the third embodiment. 115 is the time value of the clock 103 mounted on the satellite
A stored command reading unit that inputs a corrected time value 111 obtained by correcting 109 by the correction unit 105 and selects a stored command to be issued at each time.

Next, the operation will be described. Correction unit 105
By shifting the output of the clock unit 103 mounted on the artificial satellite by the predicted time shift amount, a corrected time value 111 suitable for a perturbed orbit can be output. , The stored command reading unit 115 selects a stored command to be issued.
The operation of the reading unit is similar to that of the third embodiment. The correction time value 111 is a time correction amount 110 in consideration of orbital fluctuation.
Therefore, even if the issuance of the command is managed by the time information, the stored command can be issued at the orbital position of the latitude argument which is not much different from the time of planning. Although the orbital position determining unit 102 and the clock unit 103 are shown as separate elements, these may be configured by a GPS receiving unit.

As described above, according to the fourth embodiment, it is possible to predict the amount of change in orbiting time due to orbit perturbation, similarly to the artificial satellite command device according to the invention described in the third embodiment. Using this prediction result, the time correction amount is calculated and added to the stored command execution determination time, thereby correcting the stored command execution time, thereby reducing the observation position error due to the orbit perturbation.

Embodiment 5 FIG. 7 is a block diagram showing Embodiment 5 of the present invention. Reference numeral 117 denotes planned time part data of the stored command, 118 denotes corrected time value data of the stored command, and 114 denotes command data of the stored command. Corrected time value data of stored command 11
8 is appropriately rewritten to the value of the output time correction amount 110 of the comparing unit 104. 121 calculates the sum of the planned time value data 117 and the corrected time value data 118, and the clock 103 mounted on the satellite.
This is a stored command reading unit that selects a stored command to be issued at each time according to the time value 109 of the above. The selection of the time is determined based on the sum of the planned time value data 117 and the corrected time value data 118.

Next, the operation will be described. The initial value of the correction time value data 118 of the stored command is zero,
It is appropriately rewritten to the value of the output time correction amount 110 of the comparing unit 104. The stored command reading unit 115 selects a stored command to be issued at each time according to the time value 109 of the clock unit 103. Stored command reading unit 121
Scans the planned time value data 117 and the corrected time value data 118 written in the memory at fixed time intervals, and sums the planned time value data 117 and the corrected time value data 118 to the time value 109.
Find a match. Applicable plan time value data
If there is the 117 and the correction time value data 118, the command data 114 to be combined with the data is selected and the issuing process is performed. Since the selection of the command issuance time is determined with respect to the sum of the planned time value data 117 and the corrected time value data 118, the command is shifted by the time correction amount 110 calculated by the comparing unit 104, so that it is adapted to the perturbed trajectory. The stored command can be issued at the corrected time.

Therefore, even if the command issuance is managed at the time, the stored command can be issued at the orbital position of the latitude argument which is not much different from the time of planning. Although the orbital position determining unit 102 and the clock unit 103 are shown as separate elements, these may be configured by a GPS receiving unit.

As described above, according to the fifth embodiment, similarly to the artificial satellite command device according to the third embodiment, the stored command for operating the artificial satellite is executed at the orbital position assumed when the operation plan was created. As described above, the scheduled execution time of the stored command is rewritten, and the device that receives the stored command can obtain the corrected time amount and use the information on the correction amount.

Embodiment 6 FIG. FIG. 8 is a block diagram showing Embodiment 6 of the present invention. 113 is the planned time value data of the stored command, 114 is the command data of the stored command, and 115 is the time value of the clock 103 mounted on the satellite.
According to the corrected time value 111 obtained by correcting 109 by the correction unit 105,
This is a stored command reading unit that selects a stored command to be issued at each time. Also, the stored command readout unit 115 distributes the time correction amount 119 calculated by the comparison unit 104 and the time correction amount 119 to the onboard satellite device together with the issue command.

Next, the operation will be described. Correction unit 105
By shifting the output of the clock unit 103 mounted on the artificial satellite by the predicted time shift amount, a corrected time value 111 suitable for a perturbed orbit can be output. , The stored command reading unit 115 selects a stored command to be issued.
Since the corrected time value 111 is updated by the time correction amount 110 in consideration of the orbital fluctuation, even if the issuance of the command is controlled by the time information, the stored command is stored in the orbital position of the latitude argument which does not greatly differ from the planned time. Can be issued. Also, the stored command reading unit 115 can distribute the time correction amount 110 calculated by the comparing unit 104 to the on-board device as a time correction amount 119 together with the issue command. Although the orbital position determining unit 102 and the clock unit 103 are shown as separate elements, these may be configured by a GPS receiving unit.

As described above, according to the sixth embodiment, similarly to the artificial satellite command device according to the fourth embodiment, the stored command for operating the artificial satellite is executed at the orbital position assumed when the operation plan was created. In order to correct the stored command execution time by adding a corrected time amount to the reference time at which the stored command is read, a device that receives the stored command obtains the corrected time amount. Then, the information on the correction amount can be used.

[0041]

According to the first and second aspects of the present invention, the GPS (Global Posi
By using a satellite position determining unit using a receiver or the like, it is possible to update the passage time of the orbital position of the satellite orbit, such as the ascending intersection, to the latest value. Also,
Since the collation between the planned orbital position and the actual flight orbital position can be set at any orbital position, the orbital motion after perturbation can shorten the interval from this time reference to the orbital position where time correction is required, for example, within one orbit. . Therefore, there is an effect that the amount of orbit perturbation accumulated until the time is corrected can be made smaller than in the case of the related art.

According to the third and fourth aspects of the present invention, it is possible to predict the orbital position error of the artificial satellite after the operation plan has been created, and to convert this into a time error to calculate the corrected time amount. Therefore, if the observation plan is given by the latitude argument of each orbit, there is an effect that the elapsed time from the ascending intersection passing time can be measured. Further, by measuring the orbital position and its time during the subsequent orbit, the amount of change in orbital orbiting time due to orbital perturbation can be predicted. By using the prediction result to calculate the time correction amount and correcting the scheduled execution time of the stored command, there is an effect that the observation position error due to the orbit perturbation can be reduced. The above describes observation operation, but it is also applicable to ON / OFF of equipment other than observation.

According to the fifth and sixth aspects of the invention, similarly to the artificial satellite command device according to the third and fourth aspects, it is possible to predict the amount of change in orbiting time due to orbital perturbation. Using this prediction result, the time correction amount is calculated and added to the stored command execution determination time, thereby correcting the stored command execution time, thereby reducing the observation position error due to orbital perturbation. .

According to the seventh aspect, similarly to the third and fourth aspects, the stored commands for performing the artificial satellite operation are scheduled to be executed at the orbital positions assumed when the operation plan was created. There is an effect that a device that rewrites the time and receives the stored command can obtain the corrected time amount and use the information on the correction amount.

According to an eighth aspect, similarly to the fifth and sixth aspects, the stored commands for performing the artificial satellite operation are read out so that the stored commands are executed at the orbital positions assumed when the operation plan was created. By adding the correction time amount to the reference time to be performed, the stored command execution time is corrected, and a device that receives the stored command can obtain the corrected time amount and use the information on the correction amount. effective.

[Brief description of the drawings]

FIG. 1 is a block diagram illustrating an artificial satellite onboard time correction device according to a first embodiment of the present invention.

FIG. 2 is a diagram illustrating a data table according to the first embodiment of the present invention and a conceptual diagram of time correction in observation.

FIG. 3 is a block diagram illustrating an artificial satellite-mounted time correction device according to a second embodiment of the present invention.

FIG. 4 is a block diagram illustrating an artificial satellite onboard time correction device according to a third embodiment of the present invention.

FIG. 5 is a block diagram illustrating an artificial satellite-mounted time correction device according to a fourth embodiment of the present invention.

FIG. 6 is a block diagram illustrating an artificial satellite-mounted time correction device according to a fourth embodiment of the present invention.

FIG. 7 is a block diagram illustrating an artificial satellite onboard time correction device according to a fifth embodiment of the present invention.

FIG. 8 is a block diagram illustrating an artificial satellite-mounted time correction device according to a sixth embodiment of the present invention.

FIG. 9 is a conceptual diagram illustrating the technical background of the present invention.

[Explanation of symbols]

101 data table, 102 orbit position determination unit, 1
03 Clock section, 104 comparison section, 105 correction section, 112
GPS receiving unit, 115 stored command reading unit, 120 memory correction unit, 121 stored command reading unit.

Claims (8)

[Claims] 1. An orbital position determining unit that calculates position information of an artificial satellite, a clock unit that outputs time information, a planned orbital position at the time of an artificial satellite operation plan, and a planned time at which the artificial satellite is located at the planned orbital position The data table storing the values, the orbital position determining unit and the satellite orbital position data and the time information output from the clock unit, and the expected orbital position equivalent to the orbital position determining unit output stored in the data table. An artificial unit comprising: a comparing unit that converts an artificial satellite orbital position error after operation planning into a time correction amount by comparing with the scheduled time value; and a correcting unit that adds the time correction amount to the clock output. Time correction device for satellite. 2. An orbital position determining unit for calculating position information of the artificial satellite, a clock unit for outputting time information, a planned orbital position at the time of the satellite operation plan, and a planned time at which the artificial satellite is located at the planned orbital position. The data table storing the values, the satellite orbit position data and the time information output from the orbit position determining unit and the clock unit, and the time equivalent to the clock unit output stored in the data table and the scheduled orbit position thereof And a correction unit for converting the satellite orbital position error after operation planning into a time correction amount, and a correction unit for adding the time correction amount to the clock output. Correction device. 3. An orbital position determining unit for calculating position information of the artificial satellite, a clock unit for outputting time information, a planned orbital position at the time of the satellite operation plan, and a planned time at which the artificial satellite is located at the planned orbital position. The data table storing the values, the orbital position determining unit and the satellite orbital position data and the time information output from the clock unit, and the expected orbital position equivalent to the orbital position determining unit output stored in the data table. A comparison unit that converts the satellite orbital position error after the operation plan into a time correction amount by comparing with the scheduled time value, and a memory that previously stores a command for giving a predetermined command to a device mounted on the satellite and its issue time value And a memory correction unit for correcting the command issue time value stored in the memory by the time correction amount output of the comparison unit. . 4. An orbital position determining unit for calculating position information of the artificial satellite, a clock unit for outputting time information, a planned orbital position at the time of the satellite operation plan, and a planned time at which the artificial satellite is located at the planned orbital position. The data table storing the values, the satellite orbit position data and the time information output from the orbit position determining unit and the clock unit, and the time equivalent to the clock unit output stored in the data table and the scheduled orbit position thereof A comparing unit that converts the satellite orbital position error after the operation plan into an amount of time correction by comparing with the operation plan, a memory that previously stores a command for giving a predetermined command to a device equipped with the artificial satellite and its issue time value, A memory correction unit that corrects the command issue time value stored in the memory unit by the time correction amount output of the comparison unit. 5. An orbital position determining unit for calculating position information of an artificial satellite, a clock unit for outputting time information, a planned orbital position at the time of the satellite operation plan, and a planned time at which the artificial satellite is located at the planned orbital position. The data table storing the values, the orbital position determining unit and the satellite orbital position data and the time information output from the clock unit, and the expected orbital position equivalent to the orbital position determining unit output stored in the data table. A comparison unit that converts the satellite orbital position error after the operation plan into a time correction amount by comparing with the scheduled time value, and a correction unit that adds the time correction amount output of the comparison unit to the clock unit output; An artificial satellite command device, wherein a time output from the correction unit is a command issue time. 6. An orbital position determining unit for calculating position information of an artificial satellite, a clock unit for outputting time information, a planned orbital position at the time of a satellite operation plan, and a scheduled time at which the artificial satellite is located at the planned orbital position. The data table storing the values, the satellite orbit position data and the time information output from the orbit position determining unit and the clock unit, and the time equivalent to the clock unit output stored in the data table and the scheduled orbit position thereof A comparison unit that converts the satellite orbital position error after the operation plan into a time correction amount, and a correction unit that adds the time correction amount output of the comparison unit to the clock unit output. An artificial satellite command device wherein the output time is a command issue time. 7. A memory for preliminarily storing a command for giving a predetermined command to a device mounted on an artificial satellite, an issuance time value and a time correction value, and a memory correction unit for correcting the time correction value stored in the memory. The satellite command device according to claim 3 or 4, wherein a time obtained by adding the issue time value and the time correction value is set as an issue time. 8. The satellite command device according to claim 5, further comprising a function of inputting a time correction amount output of the comparison unit and outputting the time correction amount when a command is issued.