JP4041894B2 - Method of orbiting a spare satellite into a multi-orbital satellite system - Google Patents

Description

  In a system using a plurality of satellites, a spare satellite that can be replaced with one of the plurality of satellites is placed on a standby orbit for the spare satellite, and the failure of the satellite of the above system fails. The present invention relates to a spare satellite arrangement and an orbit insertion method of a multi-orbital plane satellite system for replacing a satellite with a spare satellite and restoring the system in a short period of time.

  A method has been proposed in which a spare satellite is placed in a standby orbit for a spare satellite, and when a failed satellite occurs in the satellite system, the failed satellite is replaced with a spare satellite to restore the satellite system in a short period of time. ing. The requirements for a standby orbit for a spare satellite for this purpose are that the above replacement can be completed in a short period of time, and that the consumption of fuel for changing the satellite orbit is reduced.

  Reserve satellites are placed on a geostationary orbit with the same angle from multiple orbital planes, or on a circular orbit with a tilt angle of 0 that is the same as the near point (periphery point) of the operational orbit. Patent Document 1 discloses a method of performing conversion and putting it in the same operation orbit as that of a failed satellite. This method is characterized by using a geosynchronous orbital altitude (about 36,000 km) or a high orbit close to it, and it requires a lot of fuel just by putting it in a spare satellite orbit with a tilt angle of zero. To change the orbital plane at a larger angle from this orbit, a large amount of fuel is required again, and the number of satellites that can be put into operation orbit is limited to a very small one.

  In addition, if a spare satellite is placed in a LEO parking orbit (low altitude orbit) with the same inclination angle as the operational orbit, and the satellite in operation fails, the orbital plane of the spare satellite will be changed using perturbation of the orbit by the earth. Patent Document 2 discloses a method of waiting until it coincides with the orbit of the failed satellite, and at that stage, sequentially raising the far point and near point into the same operation orbit as the failed satellite. This method has the advantage that it requires very little fuel because it does not require orbital plane conversion, but has the disadvantage that it takes a long time to recover and takes up to about three months.

JP 2001-156696 A JP 2002-308198 A

  As described above, a spare satellite is placed in a standby orbit for a spare satellite, and when a failed satellite occurs in the satellite system, the conventional method of replacing the failed satellite with the spare satellite requires a large amount of fuel. In addition, there is a problem that it takes a long time to replace the satellite.

  In the present invention, in order to solve the problem of mass consumption of fuel in the method of Patent Document 1, the standby orbit of the standby satellite is lower than that of the method of Patent Document 1, and the far-point altitude is raised when the operation orbit is put in, The difference is that orbital plane transformation is performed at the far point of the transition elliptical orbit with a low velocity.

  Further, in order to significantly reduce the long recovery time that is a problem in the method of Patent Document 2, unlike the method of Patent Document 2, a method of performing orbital plane conversion at the intersection of the spare satellite orbital plane and the operational orbital plane, For this reason, there is no need to wait for a change in the orbital plane due to perturbation, and it is possible to recover within a few days.

  In addition, the present invention proposes a method for reducing fuel consumption as much as possible. In the conventional technology example, the method of putting the standby satellite orbit into the elliptical operation orbit has not been clarified. Furthermore, the present invention proposes an injection method suitable for an elliptical orbit while further reducing fuel consumption by a method in which the orbital plane is changed after the injection to a high altitude transition orbit.

By using the spare satellite arrangement and orbit insertion method of the multi-orbital plane satellite system of the present invention, the fuel used for orbit conversion of the spare satellite can be reduced as compared with the conventional case. In addition, the time required to restore the satellite system by replacing the troubled satellite in the operational orbit from the spare satellite orbit can be shortened compared to the conventional case. Further, the degree of freedom of the orbit that can be used as the orbit for the spare satellite can be expanded as compared with the conventional one.

  It can be confirmed that the following matters hold about the fuel consumption required when replacing a satellite in one operational orbit of the satellite system that needs to be replaced due to a failure, for example, with one spare satellite.

1) First, by arranging a spare satellite in a low altitude orbit on the equator (orbit inclination angle 0), the angles formed with all the operational orbital planes are approximately equal, and for any given said angle, In the relationship between the operation orbit and the standby orbit of the spare satellite, the speed increase amount (fuel) required for the orbital plane conversion in the worst case can be minimized.

2) Further, at the far point of the transition orbit where the near point is a low elliptical orbit, the speed of the satellite becomes small, and the amount of acceleration required for the orbital plane conversion is small.

3) Since the spare satellite passes through the ascending or descending point of the operation orbit every halfway around the low altitude orbit, there is an opportunity to enter the transition orbit approximately every hour, so that it can be restored quickly. Can be launched.

4) In addition, if an intermediate orbit is used to adjust the average near point separation angle, the present invention requires a relatively long time, but even in this case, it can be put into the same orbit as the failed satellite in about 2-3 days. Therefore, replacement can be performed in a short period of time.

5) Generally, when launching a satellite into a low orbit with a rocket, it is efficient to launch it to the east, and the standard launch sequence is based on this. In this case, the orbital inclination angle of the satellite is approximately equal to the latitude of the launch point. In order to launch to a low orbit with an approximate orbital inclination angle 0, the launch location and usable mouth bucket are extremely limited. In the conventional method, when a satellite is inserted into a circular orbit, the far point altitude of the transition orbit is approximately equal to the altitude of the operation orbit, the trajectory is changed at the far point of the transition orbit, and the near point altitude is raised to the same altitude. However, when a satellite is introduced into an elliptical operation orbit in which an orbital near-point argument is specified, such an orbital change is insufficient. However, it is possible to launch a satellite into an elliptical orbit with any near-point argument by once throwing it into a circular orbit passing through a far point or near point of the operation orbit and then performing deceleration or acceleration control at an arbitrary position. .

6) Further, at the far point of the transition orbit, not only the acceleration of the orbital plane conversion and the near point lifting as in the conventional method but also the three-dimensional velocity control that gives the velocity component in the radial direction, Can be directly input to Direct injection in this way is more efficient than implementing these separately, and the required control amount (fuel) can be reduced. In addition, since the charging is performed directly, the time required for recovery can be shortened.

7) Also, once the far point of the transition orbit is raised to a higher altitude than the operational orbit, the speed of movement of the satellite at the far point is further reduced, and the amount of control required for orbital plane conversion is greatly reduced. Additional control is required to raise to a high altitude and to return the raised far point to the altitude of the operating orbit, but the amount of control for the track surface control is greater, so the total control amount is less. I'll do it. On the other hand, the time required for recovery is increased by raising the altitude to a high altitude, but it can still be recovered in about 5 to 10 days, which is significantly shorter than the conventional technology.

8) When the orbit having the orbit inclination angle 0 is selected as the standby orbit of the spare satellite, generally, the conversion angle in the orbital plane conversion is equal to the orbit inclination angle of the operation orbit. However, when a spare satellite orbit having a non-zero orbit inclination angle is selected, in the worst case, an orbital plane conversion of an angle obtained by adding the orbit inclination angle of the operational orbit and the orbit inclination angle of the standby satellite orbit is necessary. The greater the orbital plane conversion angle, the greater the fuel saving effect for orbit conversion when using a transition orbit having a high altitude far point as in the present invention.

9) When the spare satellite is inserted into the elliptical orbit after the orbital plane conversion by the above method, it is once inserted into the circular orbit passing the far or near point of the operation orbit by the method shown above, and then the arbitrary position By performing deceleration or acceleration control with, it is possible to enter an elliptical orbit with any near-point argument.

10) When entering the operation trajectory from the operation in-plane transition trajectory, once it crosses the operation trajectory at a point near the operation in-plane transition trajectory, the speed component in the radial direction is given simultaneously with deceleration. By performing two-dimensional speed control, it is possible to directly enter the operation track. This method is more efficient than performing these separately and can reduce the amount of control (fuel) required. In addition, since the charging is performed directly, the time required for recovery can be shortened.

11) Further, a two-dimensional velocity that takes a near-point altitude of the transitional trajectory in the operational plane so as to optimize the intersection position of the operational trajectory and the operational trajectory, and gives a speed component in the radial direction simultaneously with deceleration at the intersection. If the control is performed, the control amount may be smaller than that in the above method, and in this case, fuel can be further saved.

12) Further, once the operation in-plane transition trajectory is circumscribed to the operation trajectory and decelerated at the contact point to enter the operation trajectory, the control amount may be further reduced. In this case, since the deceleration control is simple, the control itself is easy.

13) When orbiting is performed by any of the above methods, the phase (average near-point separation angle) on the orbit does not necessarily match even though the orbit can be placed in the same shape as the failed satellite. When a satellite is introduced in a sequence of the shortest period, it is necessary to control phase adjustment after throwing. If this control is divided into two at the far point, the control is put into the intermediate orbit by the first control, and if the time until the faulty satellite reaches the control point and the period of the intermediate orbit coincide, At this stage, it is possible to adjust the phase. For example, when there is a failed satellite at a position as shown in FIG. 15, if the spare satellite has reached the far point of the transition orbit, if it is directly introduced here, it will be introduced at a completely different phase, making it impossible to replace the failed satellite. . However, the control at the far point is divided into two times, for example, the first control is put into the intermediate orbit. If the time required for the faulty satellite to reach the control point and the period of the intermediate orbit match, the phases are matched at the stage where the intermediate orbit has made one round. Next, the second control may be performed and put into the operation orbit. Since the control is performed in the same direction at the same point, the total control amount does not change even when divided.

Since the above matters hold, the first requirement of the present invention is that, for example, one or a plurality of satellites in one operation orbit of a satellite system having a plurality of operation orbits due to occurrence of a failure or exceeding the service life. Is replaced with a single spare satellite, and the spare satellite is placed at a low altitude, in other words, smaller than the near-point altitude of the operational orbit Preliminary satellites are placed in a spare satellite orbit with a far-point altitude, and the spare satellites are put into the orbital plane satellite system for relocation so that the functions of the multiple satellites in the operational orbit can be performed. In the way
In the time zone when the spare satellite crosses the ascending or descending point of the operational orbit, the spare satellite is
Accelerating in the direction of travel, the far point altitude is raised to the first transition orbit where the altitude is between the near and far points of the operational orbit,
Next, at almost the far point of the first transition orbit described above, the orbital plane conversion and the control for raising the near point are performed and the operation orbital plane is thrown in,
This is to perform control in the above-described operation track plane and to put it in the operation track. Here, the operation of the satellite may be performed automatically by a command from the inside of the satellite, or may be performed by a command from the ground.

The second requirement of the present invention is a low altitude orbit with an orbital inclination angle approximately equal to the latitude of the launching point, with one or more spare satellites launched in advance to the east by a rocket. Replaced by replacing one or more of the satellites in one operational orbit of a satellite system with multiple operational orbits with one spare satellite in the above satellite orbit. When trying to perform a function similar to the previous function, reserve satellites should be placed at a low altitude as described above, and relocated so that the functions of multiple satellites in the operational orbit can be performed. In order to put a spare satellite into the multi-orbital plane satellite system,
In the time zone when the spare satellite crosses the operational orbital plane, the spare satellite is
Increase the speed in the direction of travel, raise the far point altitude to the first transition orbit where the altitude is between the near and far points of the operational trajectory,
In the vicinity of the far point of the first transition orbit, the control of both the orbital surface conversion and the near point raising is performed and the operation orbital surface is injected.
This is to perform control in the above-described operation track plane and to put it in the operation track.

Further, the third requirement of the present invention is that one or more satellites are arranged in each operational orbit on a plurality of different operational orbital planes, and one or more spare satellites have an orbital inclination angle of approximately 0 or its In a satellite system that is placed and operated in a standby satellite orbit, which is a low altitude orbit with an altitude of 2,000 km or less, approximately equal to the latitude of the launch site, a satellite in one operational orbit of the above satellite system When replacing with satellite,
In the time zone when the spare satellite crosses the operational orbital plane, the spare satellite is
Accelerate in the direction of travel, raise the far point altitude to the first transition orbit where the altitude of the operating trajectory is almost the far point,
A second transition orbit in which the altitude at the near point is substantially equal to the altitude at the far point of the first transition orbit by controlling both the trajectory change and the near point raising at the far point of the first transition orbit. To
By accelerating in the direction opposite to the traveling direction at a point near the far point of the operational orbit and decelerating so that the near point altitude is approximately equal to the near point altitude of the operational orbit, the spare satellite is It is to be put into the operation trajectory.

Further, the fourth requirement of the present invention is that one or more satellites are arranged in each operational orbit on a plurality of different operational orbital planes, and one or more spare satellites have an orbital inclination angle of approximately 0 or the same. In a satellite system that is placed and operated in a standby satellite orbit that is a low altitude orbit with an altitude of 2,000 km or less, which is approximately equal to the latitude of the launch site, a satellite in one of the above operating orbits is used as one standby orbit. When replacing with satellite,
In the time zone when the spare satellite crosses the operational orbital plane, the spare satellite is
Increasing the speed in the direction of travel, raising the far-point altitude to the first transition trajectory where the altitude at the near point of the operational trajectory is approximately equal,
In the vicinity of the far point of the first transition trajectory, both the trajectory plane conversion and the near point pull-up are controlled, and the second is a circular orbit in which the altitude at the near point is substantially equal to the far point of the first transition trajectory. Into the transition orbit of
The preliminary satellite is changed to the operational orbit by increasing the speed in the traveling direction at a point near the operational orbit's near point so that the far point altitude is approximately equal to the far point altitude of the operational orbit. It is to input.

The fifth requirement of the present invention is that in a satellite system in which one or more spare satellites are arranged and operated in advance in a low-altitude orbit having an orbital inclination angle of approximately 0 and an altitude of 2,000 km or less, When a satellite in one operational orbit of the above satellite system is replaced with a single spare satellite and the same function as the previous function is to be performed, the spare satellite is placed at a low altitude as described above. Aside from the method of orbiting a spare satellite into a multi-orbital plane satellite system for relocation so that the functions of a plurality of satellites in the operational orbit can be exhibited,
In the time zone when the spare satellite crosses directly below the ascending or descending altitude of the operational orbit, the spare satellite is
Accelerating in the direction of travel, the far point altitude is almost the rising or descending point of the above operating trajectory, and is raised near the far point to the first transition trajectory crossing the operating trajectory,
In the vicinity of the far point of the first transition orbit, orbital plane conversion and adjustment of the velocity component in the orbital plane are performed to put the spare satellite into the operational orbit.

As in the second requirement, the sixth requirement of the present invention is that a low altitude orbit with one or more spare satellites in advance having an orbital inclination angle approximately equal to the latitude of the launch point and an altitude of 2,000 km or less. In a satellite system that is arranged and operated in a spare satellite orbit, the satellite in one operational orbit of the above satellite system is replaced with one spare satellite,
In the time zone when the spare satellite crosses the operational orbital plane, the spare satellite is
Speeding up in the direction of travel, the far-point altitude is almost equal to the altitude of the intersection of the operational orbit and the orbital plane of the spare satellite, and is raised to the first transition orbit intersecting the operational orbit at the far-point,
Make the altitude of the intersection between the orbital plane of the spare satellite and the operational orbit approximately equal to the altitude at the far point, and raise it to a transition orbit that intersects the operational orbit at that far point.
The preliminary satellite is put into the operational orbit by adjusting the velocity component in the orbital plane simultaneously with the orbital plane conversion at the far point.

The seventh requirement of the present invention is that, similarly to the second requirement, one or more spare satellites are previously placed in a spare satellite orbit which is a low altitude orbit with an orbital inclination angle of approximately 0 and an altitude of 2,000 km or less. Similar to the function before replacing one or more satellites in one operational orbit of a satellite system with multiple operational orbits with one spare satellite in the above satellite orbit. Multiple orbital planes for rearranging spare satellites so that the functions of multiple satellites in the operational orbit can be performed, as described above, when spare satellites are placed at a low altitude as described above. It is about the method of orbiting a spare satellite into the satellite system.
Once the spare satellite is accelerated in the direction of travel, it is higher than the far-point altitude of the operational orbit in the time zone when one of the operational satellites crosses the ascending or descending point of the operating orbit approximately Relocate to the first transition orbit with far-point altitude,
In the vicinity of the far point of the above-mentioned transition orbit, control of the orbital plane conversion and the raising of the near point is performed, and the second transition orbit in the operational orbital plane is input,
Thereafter, a deceleration operation for lowering the far point of the second transition orbit, or in-orbit control, is performed, and the spare satellite is put into the operation orbit.

Further, the eighth requirement of the present invention is that one or more spare satellites are launched to the east by a rocket in advance and the orbit inclination angle is approximately equal to the latitude of the launch point and is a low altitude orbit with an altitude of 2,000 km or less. Before replacing a satellite system with one or more satellites with multiple operational orbits, replacing one or more satellites in one operational orbit with one spare satellite in the satellite orbit described above. In order to perform a function similar to the function of, in order to rearrange the spare satellites so that the functions of a plurality of satellites in the operational orbit can be performed at a low altitude as described above. Is a method of orbiting a spare satellite into the multiple orbital plane satellite system,
Near the time when one of the spare satellites crosses the operational orbit plane, the spare satellite is accelerated in the traveling direction to become a first transition orbit having a far point altitude higher than the far point altitude of the operational orbit. Rearrange and
In the vicinity of the far point of the first transition orbit, the control of the orbital plane conversion and the raising of the near point is performed, and the second transition orbit in the operational orbital plane is input,
Thereafter, a deceleration operation for lowering the far point of the second transition orbit, or in-orbit control, is performed, and the spare satellite is put into the operation orbit.

The ninth requirement of the present invention is that a reserve satellite having a low altitude orbit having an orbital inclination angle of approximately 0 or approximately equal to the launch point latitude and an altitude of 2,000 km or less. The satellite system with multiple operational orbits is placed in orbit, and one or more of the satellites in one operational orbit is replaced with one spare satellite in the satellite orbit before the replacement. When trying to demonstrate a function similar to the function, reserve satellites should be placed at a low altitude as described above and relocated so that the functions of multiple satellites in the operational orbit can be performed. Although it is about the method of orbital injection of the spare satellite to the multiple orbital plane satellite system,
First, a first transition orbit having a far point altitude higher than the far point altitude of the operational orbit by accelerating the spare satellite in the traveling direction in the vicinity of the time when one of the spare satellites crosses the operational orbital plane. Rearrange to
Next, in the vicinity of the far point of the first transition orbit, the control of the orbital plane conversion and the raising of the near point is performed, and the near point altitude when entering the second transition orbit in the operational orbital plane is determined as the operating orbit. The far-point altitude,
Next, the far-point altitude of the second transition orbit is lowered to the far-point altitude of the operational trajectory and inserted into the third transition orbit, which is a circular orbit,
After that, when the satellite on the third transition orbit reaches the point closest to the far point of the operation orbit, the satellite is accelerated in the direction opposite to the traveling direction of the satellite and decelerated, so that the near point of the third transition orbit is determined. Down and put the above spare satellite into operation orbit.

Further, as in the ninth requirement, the tenth requirement of the present invention is that one or more spare satellites in advance have an orbital inclination angle of approximately 0, or approximately equal to the launch latitude, and an altitude of 2,000 km or less. Is placed in a spare satellite orbit, which is a low-altitude orbit, and one or more of the satellites in one operational orbit of a satellite system having multiple operational orbits is replaced with one spare orbit in the above satellite orbit. When replacing a satellite with a function similar to the function before the replacement, reserve satellites are placed at a low altitude as described above, and the functions of multiple satellites in the above-mentioned operational orbit are exhibited. It is about the method of orbiting a spare satellite into a multi-orbital plane satellite system for relocation as possible,
First, a first transition orbit having a far point altitude higher than the far point altitude of the operational orbit by accelerating the spare satellite in the traveling direction in the vicinity of the time when one of the spare satellites crosses the operational orbital plane. Rearrange to
At the far point of the first transition orbit, the orbital plane conversion and the control of raising the near point so that the near point altitude is approximately equal to the near point altitude of the operating orbit are performed, and the spare satellite is moved within the operating orbital plane. Into the second transition orbit,
Next, the far-point altitude is lowered to enter the third transition orbit, which is a circular orbit,
After that, when the point closest to the near point of the operation orbit is almost reached, the speed is increased in the traveling direction to raise the far point, and the spare satellite is put into the operation orbit.

The eleventh requirement of the present invention is a satellite system in which one or more spare satellites are arranged and operated in advance in a spare satellite orbit which is a low altitude orbit with an orbital inclination angle of approximately 0 and an altitude of 2,000 km or less. When replacing a satellite in one operational orbit of the above satellite system with one spare satellite,
A method of relocating a spare satellite arranged in a spare satellite orbit having a far point altitude smaller than the near point altitude of the operational orbit so that the function of the satellite in the operational orbit can be exhibited,
During the time zone when one of the spare satellites crosses the ascending or descending point of the above-mentioned operational orbit, the above-mentioned spare satellite is accelerated in the direction of travel, and the far point altitude higher than the far point altitude of the above operational orbit is Rearrange to the first transition orbit with
Control of raising the near point at the far point of the above-mentioned transition orbit, where the orbital plane transformation and the near point altitude are approximately equal to the altitude at the rising or descending point of the above operating trajectory and the trajectory intersects with the above operating track at that near point. To enter the second transition orbit in the above-mentioned operation orbital plane,
The orbital plane conversion is performed at the near point of the second transition orbit, and the speed component in the orbital plane is adjusted at the same time to accelerate the spare satellite and put it into the operational orbit.

The twelfth requirement of the present invention is that, similarly to the eighth requirement, one or more spare satellites are preliminarily placed in a low altitude orbit with an orbital inclination angle approximately equal to the launch latitude and an altitude of 2,000 km or less. It is to be placed in a spare satellite orbit, and replace one or more satellites in one operational orbit of a satellite system with multiple operational orbits with one spare satellite in the above satellite orbit, When trying to perform a function similar to the function before replacement, reserve satellites should be placed at a low altitude as described above, and relocated so that the functions of multiple satellites in the operational orbit can be performed. Is about the method of orbiting a spare satellite into a multi-orbital plane satellite system,
First, a first transition orbit having a far point altitude higher than the far point altitude of the operational orbit by accelerating the spare satellite in the traveling direction in the vicinity of the time when one of the spare satellites crosses the operational orbital plane. Rearrange to
Next, acceleration is performed in the vicinity of the far point of the first transition orbit, and control of raising the near point is performed so that the altitude of the intersection between the orbital plane conversion and the orbital plane of the spare satellite and the operational orbit becomes the approximate near point altitude. , Put in the second transition orbit that intersects the operation orbit at almost the near point in the operation orbit plane,
Adjust the velocity component at the near point of the second transition trajectory,
The above-mentioned backup satellite in the second transition orbital plane is put into the operation orbit.

Further, the thirteenth requirement of the present invention is that, similarly to the ninth requirement, one or more spare satellites have an orbital inclination angle of approximately 0 or approximately equal to the launch latitude and an altitude of 2,000 km or less. Is placed in a spare satellite orbit, which is a low-altitude orbit, and one or more of the satellites in one operational orbit of a satellite system having multiple operational orbits is replaced with one spare orbit in the above satellite orbit. When replacing a satellite with a function similar to the function before the replacement, reserve satellites are placed at a low altitude as described above, and the functions of multiple satellites in the above-mentioned operational orbit are exhibited. It is about the method of orbiting a spare satellite into a multi-orbital plane satellite system for relocation as possible,
First, a first transition orbit having a far point altitude higher than the far point altitude of the operational orbit by accelerating the spare satellite in the traveling direction in the vicinity of the time when one of the spare satellites crosses the operational orbital plane. Rearrange to
Next, in the vicinity of the far point of the first transition orbit, control of the orbital plane conversion and the raising of the near point is performed, and the second transition orbit having the intersection of the operational trajectory and the two points in the operational trajectory plane is input. And
Thereafter, the speed component in the orbital plane is adjusted when passing through one of the intersections of the two points, and the spare satellite is put into the operational orbit.

As in the ninth requirement, the fourteenth requirement of the present invention is that one or more spare satellites have an orbital inclination angle of approximately 0 or approximately equal to the launch point latitude, and an altitude of 2,000 km or less. Is placed in a spare satellite orbit, which is a low-altitude orbit, and one or more of the satellites in one operational orbit of a satellite system having multiple operational orbits is replaced with one spare orbit in the above satellite orbit. When replacing a satellite with a function similar to the function before the replacement, reserve satellites are placed at a low altitude as described above, and the functions of multiple satellites in the above-mentioned operational orbit are exhibited. It is about the method of orbiting a spare satellite into a multi-orbital plane satellite system for relocation as possible,
First, a first transition orbit having a far point altitude higher than the far point altitude of the operational orbit by accelerating the spare satellite in the traveling direction in the vicinity of the time when one of the spare satellites crosses the operational orbital plane. Rearrange to
Next, in the vicinity of the far point of the first transition orbit, control of the orbital plane conversion and the raising of the near point is performed, and the second transition orbit is substantially circumscribed by the operating orbit in the operating orbital plane.
When passing through the vicinity of the outer contact, acceleration is performed in the direction opposite to the traveling direction and the vehicle is decelerated, so that the spare satellite is put into the operation orbit.

The fifteenth requirement of the present invention is a method of orbiting a spare satellite into a multi-orbital plane satellite system having any one of the first to fourteenth features.
In order to make it the same as the satellite in the operation orbit, the orbit conversion control between the transition orbits or the control to enter the operation orbit from the transition orbit is divided into two or more control operations.

  Embodiments of the present invention will be described below in detail with reference to the drawings. In the following description, specific numerical values will be given, but these are for explanation, there is no reason to limit to this value, and other requirements can satisfy the requirements of the claims. Is clear. In addition, when replacing a satellite in operation orbit with a spare satellite, it is desirable to move the satellite to be replaced from the operation orbit in advance.

  A geostationary satellite is a satellite that is on the equator and revolves at the same cycle as the Earth's rotation, while a quasi-zenith satellite is a satellite that revolves at the same cycle as the Earth's rotation, but the orbital plane tilted with respect to the equator. The satellite above. The position of such a quasi-zenith satellite as viewed from the service area on the ground changes every moment, and a time zone occurs where the line of sight cannot be seen. Therefore, a satellite system is configured using a plurality of quasi-zenith satellites. The In addition, the satellite system has a plurality of orbital surfaces.

  In the following description, in order to make a more specific comparison, a case will be described in which a failure occurs in a satellite belonging to the following satellite system, and this satellite is replaced with a spare satellite in a spare orbit. In the following description, for the sake of convenience, the satellite system is described as not including a spare satellite. However, in actual operation, the satellite system includes a spare satellite and is in an operational orbit, for example, a failure. It is intended to replace the satellite with a spare satellite.

  First, regarding the case where a satellite in the operational orbit of the quasi-zenith satellite system is replaced with a spare satellite, the respective arrangement and orbit insertion will be described below.

In addition, it is assumed that the parking orbit initially introduced by the rocket is a circular orbit having an altitude of 185 km. The orbit parameters of the quasi-zenith satellite are as follows.

  In addition, a satellite that has entered the backup satellite orbit via the parking orbit described above will replace the satellite in the operational orbit of the quasi-zenith satellite system, and the amount of acceleration (deceleration) from the parking orbit for comparison. (The unit is m / s).

For example, in the method described in Patent Document 1, the following control is necessary.

(1) In case of stationary orbit waiting (assuming launch from the equator as the best case)
Transition orbit injection 2,459
Static orbit insertion 1,479
3,938m / s total until the geostationary orbit
In-plane adjustment 8
Track plane conversion 2,388
Orbit change control 2,396m / s
Total control amount 6,334m / s

(2) Static orbit standby (assuming launch from 28.5 degrees north latitude)
Transition orbit injection 2,459
Static orbit insertion 1,837
4,296m / s total until the geostationary orbit
In-plane adjustment 8
Track plane conversion 2,388
Orbit change control 2,396m / s
Total control amount 6,692m / s

(3) Perigi altitude orbit standby (assuming launch from the equator as a plague case)
Transition orbit injection 2,384
Static orbit injection 1,481
3,865m / s total until the geostationary orbit
Orbital surface conversion 2,479
Raise distance 157
Trajectory change control 2,636m / s
Total control amount 6,501m / s

  From the above results, it can be seen that at least 6,334 m / s control is required in the method of Patent Document 1.

  In the following embodiment, it is assumed that the orbit for waiting the standby satellite is a circular orbit with an altitude of 1,000 km.

FIG. 1 and FIG. 3 are schematic views showing an example when the first and third requirements of the present invention are provided, respectively. The following examples can be given as examples that satisfy these first and third requirements. In this case, the evaluation (unit: m / s) as the total acceleration (deceleration) amount from the spare satellite orbit is as follows.
Preliminary satellite orbit insertion with mouth socket 443
Raise far-field altitude to 39,960 km 2,304
Convert the raceway surface by 45 degrees,
Thrown into a circular orbit at an altitude of 39,960 km 2,142
Decelerate at the far quasi-zenith orbit and enter the quasi-zenith orbit 149
Total control amount 5,038m / s

FIG. 4 is a schematic diagram showing an example when the fourth requirement of the present invention is provided. The following examples can be given as examples that satisfy the first and fourth requirements.
Preliminary satellite orbits in the mouth 443
Raise far-field altitude to 31,612 km 2,162
The track surface is converted 45 degrees, and the altitude is 31,612 km.
Throw in a circular orbit 2,333
Accelerate near the quasi-zenith orbit and place it in the quasi-zenith orbit 157
Total control amount 5,095m / s

FIG. 5 is a schematic diagram showing an example when the fifth requirement of the present invention is provided. The following examples can be given as examples that satisfy the first and fifth requirements.
Preliminary satellite orbit injection with rocket 443
Raise far-point altitude to 35,373 km 2,232
(Ascending intersection altitude of quasi-tentacle orbit: 35,373 km)
Transforms the orbital plane by 45 degrees and directly enters the quasi-zenith orbit 2,260
(3D speed control)
Total control amount 4,935m / s

FIG. 2 is a schematic diagram showing an example when the second requirement of the present invention is provided.
The following examples can be given as examples that satisfy the second and third requirements. This corresponds to the worst case of the relationship between the raceway surfaces.
Preliminary satellite orbit insertion with mouth socket 443
(Orbital inclination angle 28, 5 degrees)
Raise far-field altitude to 39,960 km 2,304
Convert the raceway surface to 73.5 degrees,
Thrown into a circular orbit at an altitude of 39,960 km 2,899
Decelerate at the far quasi-zenith orbit and enter the quasi-zenith orbit 149
Total control amount 5,795m / s

Next, the following example can be given as an example that satisfies the requirements of the second and fourth requirements. This also corresponds to the worst case of the relationship between the raceway surfaces.
Preliminary satellite orbit injection with rocket 443
(Orbital inclination angle 28.5 degrees)
Raise far-point altitude to 31,612 km 2,162
Convert the raceway surface to 73.5 degrees,
Thrown into a circular orbit at an altitude of 31,612 km 3,241
Accelerate near the quasi-zenith orbit and place it in the quasi-zenith orbit 157
Total control amount 6,003 m / s

FIG. 5 is also a schematic diagram showing an example when the sixth requirement of the present invention is provided.
The following examples can be given as examples that satisfy the requirements of the second and sixth requirements. This also corresponds to the worst case of the relationship between the raceway surfaces.
Preliminary satellite orbit injection with rocket 443
(Orbital inclination angle 28, 5 degrees)
Raise far-point altitude to 35,373 km 2,232
(Intersection altitude with quasi-tentacle orbit: 35,373 km)
Transform the orbital plane to 73.5 degrees and put it directly into the quasi-zenith orbit 3,088
(3D speed control)
Total control amount 5,763m / s

FIGS. 6 and 8 are schematic views showing an example in the case where the seventh and ninth requirements of the present invention are provided, respectively. The following example can be given as an example satisfying these seventh and ninth requirements.
Preliminary satellite orbit injection with rocket 443
Raise far-point altitude to 100,000 km 2,702
Convert the raceway surface by 45 degrees,
Raised to near altitude 39,960km 1,128
Lower the far point and put it into a circular orbit at an altitude of 39,960 kln 529
Decelerate at the far quasi-zenith orbit and enter the quasi-zenith orbit 149
Total control amount 4,951m / s
It can be seen that the result of the total control amount is -87 m / s, compared to the value obtained when the first and third requirements are satisfied.

FIG. 9 is a schematic diagram showing an example when the tenth requirement is provided. The following examples can be given as examples satisfying the seventh and tenth requirements.
(7), preliminary satellite orbit injection with the embodiment mouth socket of (10) 443
Raise far-field altitude to I00,000 km 2,702
Convert the raceway surface by 45 degrees,
Raised to near altitude 31,612km 1,036
Pull down the far point and put it into a circular orbit at an altitude of 31,612 km 693
Accelerate near the quasi-zenith orbit and place it in the quasi-zenith orbit 157
Total control amount 5,031m / s
It can be seen that the result of the total control amount is −64 m / s compared to the value in the case where the first and fourth requirements are provided.

FIG. 10 is a schematic diagram showing an example when the eleventh requirement is provided. The following examples can be given as examples that satisfy the seventh and eleventh requirements.
Preliminary satellite orbit injection with rocket 443
Raise far-point altitude to 100,000 km 2,702
Convert the raceway surface by 45 degrees,
Raised to near altitude 35,373 km 1,080
(Altitude of ascending intersection of quasi-zenith orbit: 35,373 km)
Direct injection into the quasi-zenith orbit at the near point (intersection with the quasi-zenith orbit) 685
(2D speed control)
Total control amount 4,910m / s
It can be seen that the result of the total control amount is −25 m / s as compared with the value when the first and fifth requirements are satisfied.

FIG. 12 is a schematic diagram showing an example when the fourteenth requirement is provided. The following examples can be given as examples that satisfy the seventh and fourteenth requirements.
Preliminary satellite orbit insertion with mouth socket 443
Raise far-point altitude to 100,000 km 2,702
Convert the raceway surface by 45 degrees and put it into the circumscribed track 1,087
Decelerate at the contact point of the orbit and directly enter the quasi-zenith orbit 617
Total control amount 4,849m / s
It can be seen that the result of this total control amount is -61 m / s compared to the value when the seventh and eleventh requirements are satisfied.

FIG. 7 is a schematic diagram showing an example when the eighth requirement is provided. The following examples can be given as examples satisfying the seventh and ninth requirements. This is also the worst case of the relationship between the raceway surfaces.
Preliminary satellite orbits in the mouth 443
(Orbital inclination angle 28, 5 degrees)
Raise far-point altitude to 100,000 km 2,702
Altitude of near point by converting the raceway surface to 73.5 degrees
Raised to 39,960 km 1,471
Lower the far point and put it in a circular orbit at an altitude of 39,960 km 529
Decelerate at the far quasi-zenith orbit and enter the quasi-zenith orbit 149
Total control amount 5,294m / s
It can be seen that the result of the total control amount is -501 m / s, compared to the value when the second and third requirements are satisfied.

FIG. 12 is a schematic diagram showing an example when the fourteenth requirement is provided. The following examples can be given as examples that satisfy the eighth and twelfth requirements. This is also the worst case of the relationship between the raceway surfaces.
Preliminary satellite orbit insertion with mouth socket 443
(Orbital inclination angle 28.5 degrees)
Raise far-point altitude to 100,000 km 2,702
Altitude of near point by converting the raceway surface to 73.5 degrees
Raised to 35,373 km 1,422
(Intersection altitude with quasi-zenith orbit: 35,373 km)
Direct injection into the quasi-zenith orbit at the near point (intersection with the quasi-zenith orbit) 685
(2D speed control)
Total control amount 5,252m / s

It can be seen that the result of the total control amount is −511 m / s compared to the value when the second and sixth requirements are satisfied.

Next, as another embodiment satisfying the eighth and twelfth requirements, the following example can be given. This is also the worst case of the relationship between the raceway surfaces.
Preliminary satellite orbit insertion with mouth socket 443
(Orbital inclination angle 28.5 degrees)
Raise far-field altitude to 300,000 km 2,922
Transform the orbital plane by 73,5 degrees and raise it to a near altitude of 35,373 km (intersection altitude with quasi-zenith orbit: 35,373 km) 543
Direct injection into the quasi-zenith orbit at a near point (intersection with the quasi-zenith orbit) 1,055
(2D speed control)
Total control amount 4,963 m / s
It can be seen that the result of the total control amount is −800 m / s as compared with the value obtained when the second and sixth requirements are satisfied.

Next, the following examples can be given as examples that satisfy the eighth and fourteenth requirements. This is also the worst case of the relationship between the raceway surfaces.
(8), Example 14 of (14) (The worst case for the relationship between the raceway surfaces)
Preliminary satellite orbit insertion with rocket 443
(Orbital inclination angle 28.5 degrees)
Raise far-point altitude to 100,000 km 2,702
The raceway surface is converted 73.5 degrees and put into the circumscribed raceway 1,430
Decelerate at the contact point of the orbit and directly enter the quasi-zenith orbit 617
Total control amount 5,192m / s
It can be seen that the result of the total control amount is −60 m / s compared to the value when the eighth and twelfth requirements are satisfied.

Next, the following example can be given as another embodiment that satisfies the eighth and fourteenth requirements. This is also the worst case of the relationship between the raceway surfaces.
Preliminary satellite orbit insertion with mouth socket 443
(Orbital inclination angle 28.5 degrees)
Raise far-field altitude to 300,000 km 2,922
Convert the raceway surface by 73.5 degrees and put it into the circumscribed raceway 545
Decelerate at the contact point of the orbit and directly enter the quasi-zenith orbit 1,011
Total control amount 4,921m / s
It can be seen that the result of the total control amount is -42 m / s, compared to the value obtained when the eighth and twelfth requirements are satisfied.

  As described above, the total control amount can be reduced by the present invention, and the weight of the propellant to be mounted on the satellite can be reduced. For example, if the total control amount is reduced to about 4,900 m / s, the effective orbit insertion weight of the satellite can be increased by about 50% as compared with the conventional stationary orbit standby. The value is great enough.

  The present invention can be applied to a quasi-zenith satellite, but is not limited to a quasi-zenith satellite, and a medium-altitude orbit satellite system configured by arranging a plurality of satellites on a plurality of orbital surfaces such as a GPS or a long ellipse. It can be used for an orbital satellite system, and when a satellite in the system fails, the failed satellite can be replaced with a spare satellite and the system can be restored in a short period of time.

It is a schematic diagram including the 1st requirement of this invention. It is a schematic diagram including the 2nd requirement of this invention. It is a schematic diagram containing the 3rd requirement of this invention. It is a schematic diagram containing the 4th requirement of this invention. It is a schematic diagram including the 5th and 6th requirements of this invention. It is a schematic diagram containing the 7th requirements of this invention. It is a schematic diagram containing the 8th requirement of this invention. It is a schematic diagram including the 9th requirement of this invention. It is a schematic diagram containing the 10th requirement of this invention. It is a schematic diagram containing the 11th and 12th requirements of this invention. It is a schematic diagram containing the 13th requirement of this invention. It is a schematic diagram containing the 14th requirement of this invention. It is a schematic diagram including the 15th requirement of this invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Operational orbit 1p Operational orbital surface 2 Spare satellite orbit 2p Preliminary satellite orbital surface 3 First transition orbit 3f Far point of first transition orbit 4 Second transition orbit

Claims (15)

One or more satellites are arranged in each of the operational orbits on a plurality of different operational orbital planes of the quasi-zenith satellite system, and the angles formed by all the operational orbital planes in advance are approximated by one or more spare satellites. In a satellite system that is operated by placing it in a standby satellite orbit 2 that is a low altitude orbit with an orbital inclination angle of approximately 0 and an altitude of 2,000 km or less, a satellite in one operational orbit 1 of the above satellite system is used. When replacing with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
During the time zone when the spare satellite crosses the ascending or descending point of the operational orbit 1, the spare satellite is accelerated in the traveling direction so that the far point altitude is between the near and far points of the operational orbit 1. Pull up to the first transition orbit 3 which is the altitude between,
Next, at the far point of the first transition orbit 3 described above, the orbital plane conversion and the control of raising the near point are performed at the same time and put into the operation orbital plane 1p.
A method for orbiting a spare satellite into a multi-orbital plane satellite system, wherein control is performed within the operational orbital plane and the operation orbit 1 is entered. Place one or more satellites in each operational orbit on different operational orbital planes of the quasi-zenith satellite system , launch one or more spare satellites in the east in advance with a rocket, and the orbit inclination angle In a satellite system that is arranged and operated in a standby satellite orbit 2 that is a low altitude orbit having an altitude of 2,000 km or less that is approximately equal to the latitude of the point, a satellite in one operational orbit 1 of the above satellite system is When replacing with a spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
During the time zone when the spare satellite crosses the surface 1p of the operational orbit 1, the spare satellite is accelerated in the traveling direction so that the far point altitude becomes the altitude between the near point and the far point of the operational orbit 1. To 1 transition orbit 3
At the far point of the first transition orbit 3, the control of both the orbital plane conversion and the near point raising is performed at the same time and put into the operation orbital plane 1p.
A method for orbiting a spare satellite into a multi-orbital plane satellite system, wherein control is performed within the operational orbital plane and the operation orbit 1 is entered. One or more satellites are arranged in each of the operational orbits on a plurality of different operational orbital planes of the quasi-zenith satellite system, and the angles formed by all the operational orbital planes in advance are approximated by one or more spare satellites. A satellite operated with a rocket launching a rocket with an orbital inclination angle of approximately 0 or just east, which is equal to the latitude of the launch point, and placed in a backup satellite orbit which is a low altitude orbit with an altitude of 2,000 km or less. In the system, a satellite in one operational orbit 1 of the above satellite system is replaced with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
In the time zone when the spare satellite crosses the surface 1p of the operational orbit 1, the spare satellite is accelerated in the traveling direction so that the far-point altitude becomes the altitude of the far point of the operational orbit 1 Pull it up to orbit 3,
A second trajectory in which the altitude at the near point is equal to the altitude at the far point of the first transition trajectory 3 by simultaneously controlling both the trajectory plane conversion and the near point pull-up at the far point of the first transition trajectory 3. Into transition orbit 4,
By performing acceleration in the direction opposite to the traveling direction at a point near the far point of the operational orbit 1 and decelerating so that the near point altitude is approximately equal to the near point altitude of the operational orbit 1, Is put into the operational orbit 1 described above, and a method for orbiting a spare satellite into a multi-orbital plane satellite system is provided. One or more satellites are arranged in each of the operational orbits on a plurality of different operational orbital planes of the quasi-zenith satellite system, and the angles formed by all the operational orbital planes in advance are approximated by one or more spare satellites. The orbital inclination angle is set to approximately 0 or just east with a rocket, and it is placed and operated in the standby satellite orbit 2 which is a low altitude orbit with an altitude of 2,000 km or less approximately equal to the latitude of the launch point. In a satellite system, a satellite in one operational orbit 1 of the above satellite system is replaced with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
During the time zone when the spare satellite crosses the surface 1p of the operational orbit 1, the spare satellite is accelerated in the traveling direction, and the far-point altitude becomes the altitude of the near point of the operational orbit 1 Pull it up to orbit 3,
A second trajectory in which the altitude at the near point is equal to the altitude at the far point of the first transition trajectory 3 is obtained by controlling both the orbital plane conversion and the near point raising at the far point of the first transition trajectory 3. Into the transition orbit 4 of
By speeding up in the traveling direction at a point in the vicinity of the near point of the operational orbit, the far point altitude is made approximately equal to the far point altitude of the operational orbit 1 so that the spare satellite is A method of orbiting a spare satellite into a multi-orbital satellite system, wherein One or more satellites are arranged in each of the operational orbits on a plurality of different operational orbital planes of the quasi-zenith satellite system, and the angles formed by all the operational orbital planes in advance are approximated by one or more spare satellites. In a satellite system that is operated by placing it in a standby satellite orbit 2 that is a low altitude orbit with an orbital inclination angle of approximately 0 and an altitude of 2,000 km or less, a satellite in one operational orbit 1 of the above satellite system is used. When replacing with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
In the time zone in which the spare satellite crosses the ascending or descending altitude of the operational orbit 1, the spare satellite is accelerated in the traveling direction so that the far-point altitude rises in the operational orbit 1. It becomes an intersection or descending intersection, and at that far point, it is raised to the first transition orbit 3 that intersects the operation orbit,
The spare satellite is directly introduced into the operational orbit 1 by performing three-dimensional velocity control at the far point of the first transition orbit 3 by changing the orbital plane and adjusting the velocity component in the orbital plane. The orbital method of the backup satellite to the multi-orbital plane satellite system. Place one or more satellites in each operational orbit on different operational orbital planes of the quasi-zenith satellite system , launch one or more spare satellites in the east in advance with a rocket, and the orbit inclination angle In a satellite system that is arranged and operated in a standby satellite orbit 2 that is a low altitude orbit having an altitude of 2,000 km or less that is approximately equal to the latitude of the point, a satellite in one operational orbit 1 of the above satellite system is When replacing with a spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
During the time zone when the spare satellite crosses the surface 1p of the operational orbit 1, the spare satellite is accelerated in the traveling direction so that the far-point altitude is higher than the operational orbit 1 and the orbital plane of the spare satellite. At the height of the intersection of the
The altitude of the intersection between the orbital plane 2p of the spare satellite and the operational orbit 1 is set as the altitude at the far point, and the transitional orbit 3 intersecting the operational orbit 1 at the far point is raised.
A multiple orbital plane satellite characterized in that the spare satellite is directly introduced into the operational orbit 1 by adjusting the velocity component in the orbital plane by three-dimensional velocity control at the same time as the orbital plane conversion at the far point. How to put orbit of a spare satellite into the system. One or more satellites are arranged in each of the operational orbits on a plurality of different operational orbital planes of the quasi-zenith satellite system, and the angles formed by all the operational orbital planes in advance are approximated by one or more spare satellites. In a satellite system that is operated by placing it in a standby satellite orbit 2 that is a low altitude orbit with an orbital inclination angle of approximately 0 and an altitude of 2,000 km or less, a satellite in one operational orbit 1 of the above satellite system is used. When replacing with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone in which said spare satellite crosses directly under the ascending node or descending node of the operational track 1, and accelerated the above spare satellite in the traveling direction, once higher than the altitude apogee of the operational track 1 Relocating to the first transition trajectory 3 with a far point altitude,
At the far point of the transition trajectory, the trajectory plane conversion and the control of raising the near point are simultaneously performed, and the second transition trajectory 4 in the surface 1p of the operational trajectory 1 is input,
Thereafter, a deceleration operation for lowering the far point of the second transition orbit 4 or in-orbit control is performed, and the above-mentioned reserve satellite is put into the operation orbit 1. Orbit insertion method. Place one or more satellites in each of the operational orbits on the different operational orbital planes of the quasi-zenith satellite system , launch them with a rocket to the east, and orbital tilt angle is approximately equal to the launch latitude. In a satellite system in which one or more spare satellites are arranged and operated in advance on a spare satellite orbit 2 which is a low altitude orbit of 2,000 km or less, a satellite in one operational orbit 1 of the above satellite system is replaced with one spare satellite. When replacing with satellites ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone in which said spare satellite crosses the operational raceway surface 1 above the pre satellite traveling direction accelerated and once said operation of track 1 apogee first with a high degree higher apogee altitude than Rearrange to transition orbit 3,
At the far point of the first transition orbit 3, the control of the orbital plane conversion and the near point raising is performed at the same time , and the second transition orbit 4 in the surface 1p of the operational orbit 1 is introduced,
Thereafter, a deceleration operation for lowering the far point of the second transition orbit 4 or in-orbit control is performed, and the above-mentioned reserve satellite is put into the operation orbit 1. Orbit insertion method. One or more satellites are arranged in each operational orbital plane in different operational orbital planes of the quasi-zenith satellite system, and the orbital inclination angle is such that the angles formed by all the operational orbital planes are approximately equal. A satellite that is launched with a rocket at 0 or just east, and is operated by placing one or more spare satellites in advance in a spare satellite orbit that is a low altitude orbit with an altitude of 2,000 km or less, which is approximately equal to the latitude of the launch point In the system, when a satellite in one operational orbit of the above satellite system is replaced with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone spare satellite crosses the operational raceways above, the preliminary satellite, the first transfer orbit with apogee higher apogee altitude than advanced once said operational orbit and accelerated in the traveling direction Rearrange to
At the far point of the first transition orbit, the control of the orbital plane conversion and the raising of the near point is performed at the same time, and the near point altitude at the time of entering the second transition orbit in the operational orbital plane is set as the far point altitude of the operating orbit. , The far point altitude of the second transition orbit is lowered to the far point altitude of the operational trajectory and inserted into the third transition orbit which is a circular orbit, and then the satellite on the third transition orbit is closest to the far point of the operational orbit A plurality of orbits characterized by lowering the near point of the third transition orbit by decelerating by accelerating in the direction opposite to the traveling direction of the satellite when reaching the operational orbit A method of orbiting a spare satellite into an area satellite system. One or more satellites are arranged in each operational orbital plane in different operational orbital planes of the quasi-zenith satellite system, and the orbital inclination angle is such that the angles formed by all the operational orbital planes are approximately equal. A satellite that is launched with a rocket at 0 or just east, and is operated by placing one or more spare satellites in advance in a spare satellite orbit that is a low altitude orbit with an altitude of 2,000 km or less, which is approximately equal to the latitude of the launch point In the system, when a satellite in one operational orbit of the above satellite system is replaced with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone spare satellite crosses the operational raceways above, the preliminary satellite, the first transfer orbit with apogee higher apogee altitude than advanced once said operational orbit and accelerated in the traveling direction Rearrange to
At the far point of the first transition trajectory, the orbital plane conversion and the control of raising the near point where the near point altitude is approximately equal to the near point altitude of the operating trajectory are simultaneously performed, and the spare satellite is moved within the operating orbital plane. Into the second transition orbit of
Next, the far-point altitude is lowered to enter the third transition orbit, which is approximately a circular orbit,
After that, when a point closest to the near point of the operational orbit is reached, the speed is increased in the traveling direction, the far point is raised, and the spare satellite is put into the operational orbit. Orbit insertion method of spare satellite. One or more satellites are arranged in each operational orbital plane in different operational orbital planes of the quasi-zenith satellite system, and the orbital inclination angle is such that the angles formed by all the operational orbital planes are approximately equal. In a satellite system in which one or more spare satellites are arranged and operated in advance in a spare satellite orbit 2 which is a low altitude orbit at an altitude of 2,000 km or less at 0, a satellite in one operational orbit 1 of the above satellite system is When replacing with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone in which said spare satellite crosses directly under the ascending node or descending node of the operational track 1, and accelerated the above spare satellite in the traveling direction, once higher than the altitude apogee of the operational track 1 Relocating to the first transition trajectory 3 with a far point altitude,
At a far point of the transition trajectory 3, the trajectory plane transformation and the near point altitude are approximately equal to the ascending or descending altitude of the operational trajectory 1 and become a trajectory that intersects the operational trajectory 1 at the near point. Simultaneously with the pulling up control, the second transition orbit of 1p in the above-mentioned operation orbit plane is inserted,
A plurality of orbits characterized in that orbital plane transformation is performed near the second transition orbit 3 and at the same time the velocity component in the orbital plane is adjusted by two-dimensional velocity control and the spare satellite is put into an operational orbit. A method of orbiting a spare satellite into an area satellite system. Place one or more satellites in each of the operational orbits on the different operational orbital planes of the quasi-zenith satellite system , launch them with a rocket to the east, and orbital tilt angle is approximately equal to the launch latitude. In a satellite system in which one or more spare satellites are arranged and operated in advance on a spare satellite orbit 2 which is a low altitude orbit of 2,000 km or less, a satellite in one operational orbit 1 of the above satellite system is replaced with one spare satellite. When replacing with satellites ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone in which said spare satellite across the face 1p of the operational track 1, the preliminary satellite, first with advanced once increased speed in the traveling direction higher than the altitude apogee of the operational track 1 apogee Rearranged in 1 transition trajectory 3,
Accelerate at the far point of the first transition orbit 3 above, and simultaneously control the orbital plane conversion and the raising of the near point where the altitude of the intersection between the orbital surface of the spare satellite and the above orbital 1 becomes the near point altitude. The second transition track 4 that intersects the operation track 1 at a near point in the track surface is inserted,
Adjust the velocity component at the near point of the second transition orbit 4 by the two-dimensional velocity control ,
A method for orbiting a spare satellite into a multi-orbital plane satellite system, wherein the above-mentioned spare satellite in the second transition orbit plane is thrown into an operational orbit 1. One or more satellites are arranged in each operational orbital plane in different operational orbital planes of the quasi-zenith satellite system, and the orbital inclination angle is such that the angles formed by all the operational orbital planes are approximately equal. Launched with a rocket at 0 or just east, one or more spare satellites are pre-arranged and operated in reserve satellite orbit 2, which is a low altitude orbit approximately equal to the latitude of the launch point and altitude of 2,000 km or less In a satellite system, a satellite in one operational orbit 1 of the above satellite system is replaced with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone in which said spare satellite across the face 1p of the operational track 1, the preliminary satellite, first with advanced once increased speed in the traveling direction higher than the altitude apogee of the operational track 1 apogee Rearranged in 1 transition trajectory 3,
At the far point of the first transition orbit 3, the control of the orbital plane conversion and the near point raising is performed at the same time , and the second transition orbit 4 having the intersection of the operational trajectory 1 and the two points in the operational trajectory plane is input. And
After that, the velocity component in the orbital plane is adjusted when passing through one of the intersections of the two points, and the spare satellite is put into the operational orbit 1. Orbit insertion method of spare satellite. One or more satellites are arranged in each operational orbital plane in different operational orbital planes of the quasi-zenith satellite system, and the orbital inclination angle is such that the angles formed by all the operational orbital planes are approximately equal. Launched with a rocket at 0 or just east, one or more spare satellites are pre-arranged and operated in reserve satellite orbit 2, which is a low altitude orbit approximately equal to the latitude of the launch point and altitude of 2,000 km or less In a satellite system, a satellite in one operational orbit 1 of the above satellite system is replaced with one spare satellite ,
When the spare satellite orbit plane 2p to which the spare satellite orbit 2 belongs and the operational orbit plane 1p to which the operational orbit 1 belongs intersect at a significant angle,
The spare satellite enters the spare satellite orbit 2 through a parking orbit,
The time zone in which said spare satellite across the face 1p of the operational track 1, the preliminary satellite, first with advanced once increased speed in the traveling direction higher than the altitude apogee of the operational track 1 apogee Rearranged in 1 transition trajectory 3,
At the far point of the first transition trajectory 3, the trajectory plane conversion and the control of raising the near point are performed at the same time , and the second transition trajectory 4 that is generally circumscribed by the operating trajectory in the operating trajectory plane is input.
When the satellite passes through the vicinity of the outer contact, it accelerates in the direction opposite to the traveling direction and decelerates, thereby introducing the spare satellite into the operational orbit 1. Orbit insertion method.   In order to make the satellite phase (average near-point separation angle) in the operational orbit the same as the satellite in the operational orbit that is replaced with the spare satellite, orbit conversion control between transition orbits, or control that enters the operational orbit from the transition orbit 15. The method of orbiting a spare satellite into a multi-orbital plane satellite system according to claim 1, wherein the operation is divided into two or more control operations.