Patent Description:
A satellite is subjected to various disturbances from the outside. In particular, in the case of a geostationary orbit satellite, a torque generated as a solar radiation pressure continuously acts on a solar panel of the satellite is a main disturbance factor. <FIG> illustrates the effect of the solar radiation pressure according to a revolution of the geostationary orbit satellite. As illustrated, a Zs axis of the satellite always faces the earth, whereas the solar panel always faces the sun. In this case, since the solar radiation pressure acts on the solar panel, the solar panel continuously receives a force in one direction, and accordingly, angular momentum, that is, momentum (on a Xs/Zs plane of the satellite in <FIG>), is accumulated at a constant rate in a direction perpendicular (Xes axis in <FIG>) to the earth/sun direction.

Meanwhile, the satellite is provided with an actuator for attitude control, and representative examples thereof include a thruster and a reaction wheel. The thruster is a device that controls attitude by injecting fuel. In other words, the thruster is an external momentum exchange device type, and can change the momentum of the entire satellite, but cannot perform ultra-precision attitude control of the entire satellite. The reaction wheel is a device that controls attitude by turning a wheel with a motor. In other words, the reaction wheel is an internal momentum exchange device type, and cannot change the momentum of the entire satellite, but enables ultra-precise attitude control of the entire satellite.

As described above, when the attitude of the satellite is controlled to continuously maintain the earth-oriented attitude with the reaction wheel while a disturbance torque by the solar radiation pressure is continuously acting, the momentum is accumulated in the Xes axis direction by the disturbance torque, and stored in the reaction wheel. Reducing the momentum stored in such a reaction wheel is called a momentum dump. When the momentum dump is not performed at an appropriate cycle, the speed of the reaction wheel reaches a maximum speed limit or the rotation direction is changed and the speed temporarily becomes <NUM> (zero speed, zero-crossing). When the reaction wheel reaches the maximum speed limit, it becomes impossible to perform attitude control because it can no longer generate torque in the rotational direction. On the other hand, when the reaction wheel reaches the zero speed, static friction is applied to a bearing to temporarily affect the precise attitude control of the satellite, so the performance of missions such as ground observation is impeded and the lubrication action of the bearing is not smooth, resulting in affecting characteristics and life of the bearing.

For this reason, the conventional geostationary orbit satellite has been made to periodically perform the process of dumping the momentum stored in the reaction wheel mainly by using a thruster. This process is called the momentum management of the geostationary orbit satellite, and there are several factors to consider in the momentum management as follows.

First, the momentum capacity of the reaction wheel needs to be considered. As a wheel with a large momentum capacity is used, the time it takes for the speed of the reaction wheel to reach the maximum speed limit or the zero speed may be delayed, but there is a problem of increasing the weight and price.

Second, the number and arrangement direction of reaction wheels should be considered. For three-dimensional attitude control, at least three reaction wheels are required to perform a linear span of a three-dimensional space. However, in practice, it is common to use <NUM> or more reaction wheels to prepare for failure. In this case, as a large number of reaction wheels are used, the total momentum capacity of the reaction wheels increases, but there is also a problem of increasing the weight and price. In addition, even if the same number of reaction wheels are used, the three-dimensional momentum capacity generated by all the reaction wheels varies depending on which direction the reaction wheels are arranged.

Third, the cycle and schedule of the momentum dump should be considered. The more frequently the momentum dump using the thruster is performed, the more it is possible to prevent the speed of the reaction wheel from reaching the maximum speed limit or the zero speed in advance. However, during the momentum dump using the thruster, the precise attitude control of the satellite cannot be maintained and the mission performance needs to be paused, and when the momentum dump cycle using the thruster is too short, there is a problem in that the mission performance efficiency decreases. In addition, when the dump is performed at the same local time every time, only a specific thruster is mainly used, which adversely affects the operation of the device.

Among these various considerations, the cycle and schedule of the momentum dump will be described in more detail as follows. <FIG> illustrates an embodiment in which four thrusters are arranged on the Ys-axis plane of the satellite, and <FIG> illustrates an embodiment of a thruster-based momentum dump scenario for the satellite in which the thruster is disposed as illustrated in <FIG>. As in the description of <FIG>, the solar panel is installed in a Ys-axis direction of a fuselage in the satellite of this embodiment, and thus, the external torque is continuously applied by the solar radiation pressure. In order to maintain the earth-oriented attitude against the action of the external torque, the momentum (angular momentum) is accumulated and stored in the reaction wheel responsible for the attitude control, and the stored momentum is appropriately dumped using the thruster. Since it is well known that it is most efficient to perform the momentum dump when the thruster is located farthest from the Ys axis of the fuselage in the sun direction, in the case of <FIG>, it is efficient to perform the momentum dump at local times <NUM>-α/<NUM>, <NUM>+α/<NUM>, <NUM>-α/<NUM>, and <NUM>+α/<NUM>, respectively, according to the respective positions on the fuselage of thrusters #<NUM> to <NUM>. Although the number of thrusters is different in the Chollian 2A satellite, which is developed and currently under the supervision of the Korea Aerospace Research Institute, the same method in principle as the momentum compensation maneuvering technique has been used. The momentum management is described in more detail in the Chollian 2A satellite, "Chollian 2A Orbital Maintenance Maneuvering and Wheel Momentum Offloading Performance Analysis" (Hyung-Joo Yoon, Young-Woong Park, Dae-Kwan Kim, Geun-Ju Park, Proceedings of the <NUM> Spring Conference of the Korean Society of Aeronautics and Space Sciences, <NUM>, 'Prior Document <NUM>'). According to Prior Document <NUM>, the Chollian 2A is operated to perform the momentum dump once a day (<NUM> hours), and the local time for performing the momentum dump is changed every few months to use the same thruster as possible. It is known that it is possible to obtain a result of satisfying the requirements that the reaction wheel does not reach the maximum continuous speed and the zero speed by the momentum management.

In this way, the cycle and schedule of the momentum dump are determined to perform the momentum dump cyclically once a day, and thus, the satellite equipped with the reaction wheel whose momentum capacity and number are appropriately determined to digest the accumulated momentum due to the disturbance torque according to the solar radiation pressure for <NUM> hours is currently being successfully operated. However, there are always variables that may lead to unpredictable situations. For example, when the situation where the urgent and high-priority mission performance is required lasts for an unexpectedly long time (since the momentum dump should not be performed during the mission performance), the momentum may be continuously accumulated for more than <NUM> hours. Of course, the momentum capacity of the reaction wheel is determined to be digestible even if the momentum is accumulated for more than <NUM> hours by applying a sufficient safety index, but this method needs to adopt the reaction wheel with larger capacity, which increases the weight and cost of the satellite. Considering this, for example, even in the case of the satellite that is designed to perform the momentum dump in any cycle and is well operated, there is always a need for an improvement plan to improve safety and efficiency by improving the operation method in the same specification.

(Non-Patent Document <NUM>) <NUM>.

An object of the present disclosure is to provide an offset-applied momentum dump method for a satellite reaction wheel, in which an appropriate offset is applied to an originally designed momentum dump to enable safer and more efficient operation of a satellite.

In one general aspect, a momentum dump method for a satellite reaction wheel operated to dump momentum as much as a known momentum dump amount according to a predetermined dump cycle may include: an offset application requesting step in which an offset application is requested during the momentum dump to the satellite; and an offset momentum dumping step in which the momentum as much as a predetermined offset dump amount is dumped from the reaction wheel to generate a momentum offset in a direction opposite to a direction in which the momentum is accumulated. In this case, the offset dump amount may be determined as a value smaller than the momentum dump amount.

In addition, the offset-applied momentum dump method for a satellite reaction wheel may be applied during a first operation of the satellite, or may be applied during a normal operation of the satellite.

Specifically, when the momentum dump method for a satellite reaction wheel is applied to the satellite that intends to go into orbit and start an operation, a step of making the momentum stored in the reaction wheel become <NUM> by performing initial setting to start the operation of the satellite on the orbit, the offset application request step, and the offset momentum dump step may be sequentially performed, so, after a momentum offset is generated in the reaction wheel, the satellite may be operated to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle.

In addition, when the momentum dump method for a satellite reaction wheel is applied to the satellite in operation to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle, the offset application request step, a step in which <NUM> dump cycle being performed at a time when the offset application request step is performed is completed, and thus, the momentum as much as the momentum dump amount is dumped in the reaction wheel so that the stored momentum becomes <NUM>, and the offset momentum dump step may be sequentially performed, so, after a momentum offset is generated in the reaction wheel, the satellite may be operated to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle.

In addition, the momentum dump method for a satellite reaction wheel may include a method of determining the momentum dump amount, and the method of determining the momentum dump amount may operate any one selected from the satellite, another satellite having the same specification as the satellite, or a satellite simulator designed to be equivalent to the satellite to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle, and may include a basic momentum accumulation step of accumulating the momentum due to disturbance torque due to solar radiation pressure in the reaction wheel for <NUM> dump cycle, and a basic dump amount calculation step of calculating the momentum accumulated in the basic momentum accumulation step as the momentum dump amount or determining a value selected from a predetermined momentum dump amount database as the momentum dump amount.

In addition, the momentum dump method may further include, after the offset momentum dump step, a long-term satellite mission performance step of performing the satellite mission without the momentum dump for <NUM> dump cycle or more after the offset momentum dump step.

In this case, when <NUM> dump cycle is <NUM> hours and a long-term satellite mission performance period is <NUM> hours, the momentum offset may be determined as a value corresponding to the accumulated amount of momentum due to solar radiation pressure for a <NUM>/<NUM> long-term satellite mission performance period, that is, <NUM> hours.

In addition, when <NUM> dump cycle is <NUM> hours and the long-term satellite mission performance period is <NUM> hours, the momentum offset may be determined as a value corresponding to the accumulated amount of momentum due to solar radiation pressure for a <NUM>/<NUM> long-term satellite mission performance period, that is, <NUM> hours.

According to the present disclosure, it is possible to enable safer and more efficient operation of a satellite by applying an appropriate offset to an originally designed momentum dump cycle. Specifically, for a satellite designed to perform a momentum dump in a predetermined cycle, as an example, when a reaction wheel is first operated, a momentum of <NUM>/<NUM> cycle is dumped while the wheel speed is <NUM>, thereby making the accumulated momentum of the reaction wheel equal to a non-zero momentum offset. When the momentum is accumulated again in this state, the time when the original momentum dump should be performed may be much later than the time when the original momentum dump should be performed. As described above, according to the present disclosure, by applying the offset to the momentum dump, it is possible to delay the time when the momentum dump is to be performed and perform the satellite mission without the momentum dump for an extended period of time, thereby greatly improving the efficiency of satellite operation.

In addition, according to the present disclosure, by applying the momentum offset to delay the momentum dump time, it is possible to accumulate the momentum for <NUM> cycle even with a reaction wheel assembly with momentum capacity that is substantially less than that of the original <NUM> cycle, and thus, it is possible to reduce the weight and cost of the satellite by alleviating the requirements for the momentum capacity of the reaction wheel. In addition, considering this effect in another direction, the offset is applied, and thus, a less load is applied to the reaction wheel as much, so it is possible to reduce the power consumption and extend the life of the reaction wheel, thereby improving the safety of the satellite.

Hereinafter, an offset-applied momentum dump method for a satellite reaction wheel according to the present disclosure having the configuration as described above will be described in detail with reference to the accompanying drawings.

In general, the satellite reaction wheel is operated to dump momentum as much as the momentum dump amount of the known <NUM> dump cycle amount according to a predetermined dump cycle. That is, momentum is accumulated and stored in the reaction wheel for <NUM> dump cycle, and the momentum dump is performed immediately after <NUM> dump cycle, and thus, an operation of making the momentum stored in the reaction wheel become <NUM> is repeatedly performed. For ease of understanding, for example, when the momentum accumulated in the reaction wheel for <NUM> dump cycle is <NUM>, a momentum of [<NUM> to <NUM>] is stored in the reaction wheel while an operating time is [<NUM> to <NUM> dump cycle].

First, the process of determining the momentum dump amount while performing the momentum dump on the satellite reaction wheel will be described step-by-step as follows. When normally operating the satellite, the method for determining the momentum dump amount may include a basic momentum accumulation step and a basic dump amount calculation step. In other words, the determination of the momentum dump amount is made in an operation of operating any one selected from the satellite, another satellite having the same specification as the satellite, or a satellite simulator designed to be equivalent to the satellite to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle. That is, the "reaction wheel" in the following is to be understood as referring to the reaction wheel included in any one selected from the satellite to which the momentum dump method of the present disclosure is actually applied, another satellite having the same specification as the satellite, or the satellite simulator designed to be equivalent thereto.

In the basic momentum accumulation step, the momentum is accumulated due to the disturbance torque due to the solar radiation pressure in the reaction wheel for <NUM> dump cycle. In this case, the dump cycle may be appropriately determined as desired according to the purpose or necessity of the user, and may be usually determined to be <NUM> hours in accordance with the cycle of the rotation of the earth. Of course, it is natural that the dump cycle may be determined differently without limit depending on the satellite mission performance schedule.

In the basic dump amount calculation step, the momentum accumulated in the basic momentum accumulation step may be calculated as the momentum dump amount. That is, the momentum dump amount is determined by the momentum value accumulated by the solar radiation pressure for <NUM> dump cycle. Alternatively, in the basic dump amount calculation step, a value selected from a predetermined momentum dump amount database may be determined as the momentum dump amount. Although the momentum dump amount has slight variation, the momentum dump amount is a value that converges to an approximately constant value. As described above, the momentum dump amount may be newly measured every dump cycle to be newly determined, but may be determined as a certain specific constant value. However, this value will also appear to have little variation between the values measured every day, but since a non-negligible level of variations may be generated gradually depending on the Earth's orbital cycle, as described above, it is preferable to create the momentum dump amount database with the momentum dump amount measured for every dump cycle. As described above, the predetermined momentum dump amount database may be used, for example, by selecting and applying an appropriate momentum dump amount constant value for each date or period from the momentum dump amount database.

Without the concept of the momentum dump in the present disclosure, when the satellite is operated to dump the momentum as much as the momentum dump amount of the known <NUM> dump cycle amount according to a predetermined dump cycle, the conventional satellite momentum management process will be described in more detail below.

The momentum as much as the momentum dump amount is dumped from the reaction wheel every <NUM> dump cycle, and the stored momentum becomes zero. <FIG> illustrates the conventional momentum dump method and the momentum stored in the reaction wheel, in the satellite that performs the momentum dump with <NUM> hours as <NUM> dump cycle. As indicated by a light arrow (dumped momentum) in the graph on the left of <FIG>, when the momentum as much as the momentum dump amount is dumped without applying a momentum offset (that is, momentum offset = <NUM>), the amount of momentum stored in the reaction wheel becomes zero (momentum = <NUM>). A dark arrow (accumulated Momentum for <NUM> hrs) indicates the momentum that is again accumulated for <NUM> hours (<NUM> dump cycle), and is the same amount as the momentum dump amount indicated by the light arrow.

The right of <FIG> is a graph illustrating an aspect, in which the momentum is accumulated and stored in the reaction wheel, in a fuselage coordinate system of the satellite rotating in a cycle of <NUM> hours. As illustrated, immediately after the momentum dump is performed (+<NUM> after the dump) (since the momentum dump was completed in the previous cycle), it can be seen that the momentum stored in the reaction wheel is <NUM> and is gradually accumulated with the passage of time, and thus, the amount stored increases. In this case, since the fuselage of the satellite always faces the earth as illustrated in <FIG>, the satellite rotates in a cycle of <NUM> hours, and thus, the stored momentum increases in a spiral shape. Normally, since <NUM> dump cycle is <NUM> hours, up to +<NUM> is shown in a solid line after the dump is performed, but up to +<NUM> is shown in a dotted line assuming that the momentum dump may not be performed due to the unexpected reasons (for example, performing an urgent satellite mission outside the schedule).

As described above, even for a satellite that is designed and operated well to perform the momentum dump in a certain cycle, when the situation in which the urgent and high-priority mission performance is required lasts for an unexpectedly long time (since the momentum dump should not be performed during the mission performance), there is always the possibility that the momentum is accumulated for more than <NUM> hours. It would be nice if the momentum capacity of the reaction wheel could be designed sufficiently to prepare for such a case, but as the momentum capacity increases, the problem arises that the weight and size also increase.

In the present disclosure, the improved momentum dump method for a satellite reaction wheel is proposed so that the satellite may be operated more safely and efficiently by applying an appropriate offset to the originally designed momentum dump management. First, a specific embodiment will be described with reference to <FIG> and <FIG>, and the momentum dump method for a satellite reaction wheel of the present disclosure will be described more generally with reference to <FIG> and <FIG>.

<FIG> is a diagram illustrating a momentum dump method and momentum stored in a reaction wheel according to a first embodiment of the present disclosure. As in the description of <FIG>, in a satellite that performs momentum dump with <NUM> hours as <NUM> dump cycle, in the first embodiment, as illustrated in the left of <FIG>, the momentum is dumped so as to have a momentum offset of <NUM> hours (<NUM>/<NUM> cycle) in a direction opposite to the direction in which the momentum is accumulated. The momentum is again accumulated in the reaction wheel of the satellite for <NUM> cycle from immediately after the dump, but since the momentum offset of a <NUM>/<NUM> cycle amount is applied, the magnitude of the momentum stored in the reaction wheel of the satellite even after <NUM> cycle does not exceed a <NUM>/<NUM> cycle amount.

The right of <FIG> is a graph illustrating an aspect, in which the momentum is accumulated and stored, in the fuselage coordinate system of the satellite rotating in a cycle of <NUM> hours. As illustrated, at lapse of +<NUM> after the dump, the momentum offset generated in the previous cycle, so the stored momentum is not <NUM> but has a value corresponding to the momentum offset. When the momentum is accumulated in the reaction wheel in this state, it can be seen that the storage momentum becomes <NUM> when <NUM> hours have elapsed (+<NUM>) after the dump, and then, the stored amount increases again. The right of <FIG> also illustrates the stored amount to a 36th hour beyond <NUM> hours, and it can be seen that the amount of momentum that the reaction wheel needs to store significantly decreases when compared with the right of <FIG> at a 24th hour (<NUM>), a 36th hour (<NUM>), or the like.

<FIG> is a diagram illustrating a momentum dump method and momentum stored in a reaction wheel according to a second embodiment of the present disclosure. Also, as in the description of <FIG>, in the satellite that performs the momentum dump with <NUM> hours as <NUM> dump cycle, in the second embodiment, the amount of momentum that the reaction wheel needs to store to prepare for the case where the dump may not be performed for <NUM> hours is to be minimized. As illustrated in the left of <FIG>, the momentum is dumped by applying a momentum offset of <NUM> hours (<NUM>/<NUM> cycle), which is half of <NUM> hours, in a direction opposite to the direction in which the momentum is accumulated. When <NUM> hours (<NUM>/<NUM> cycle) after the dump lapses, the momentum stored in the reaction wheel becomes <NUM>, and after <NUM> hours (<NUM> cycle), the momentum of <NUM>/<NUM> cycle is stored. When the dump is not performed after <NUM> hours (<NUM> cycle), and thus, <NUM> hours lapse, the magnitude of the momentum stored in the reaction wheel corresponds to <NUM>/<NUM> of the accumulated amount of <NUM> cycle. That is, the momentum may be accumulated without performing the dump for <NUM> hours (<NUM> cycles) by using momentum capacity corresponding to <NUM>/<NUM> accumulated for <NUM> hours (<NUM> cycle).

The right of <FIG> is a graph illustrating an aspect, in which the momentum is accumulated and stored in the reaction wheel, in the fuselage coordinate system of the satellite rotating in a cycle of <NUM> hours. As in the right of <FIG> (the first embodiment), at lapse of +<NUM> after the dump, the value corresponding to the momentum offset is provided, but the momentum offset value is larger than that in the first embodiment. When the momentum is accumulated in the reaction wheel in this state, it can be seen that the storage momentum becomes <NUM> at a 18th hour (<NUM>), and then, the stored amount increases again. When compared with the right drawings of <FIG> and <FIG> at a 24th hour (<NUM>), a 36th hour (<NUM>), etc., compared to the original operation method, when the dump may not be performed for <NUM> hours, it can be seen that the stored amount of momentum much more decreases than the first embodiment.

As described above, in the present disclosure, as illustrated in the first and second embodiments, an appropriate amount of momentum offset is generated in the direction opposite to the direction in which the momentum is accumulated. To describe the momentum dump method for a satellite reaction wheel of the present disclosure in more detail, the present disclosure may include an offset application request step and an offset momentum dump step.

In the offset application request step, the offset application is requested when the momentum is dumped to the satellite. As described above, the basic premise is that the satellite is typically operated to dump the momentum as much as the known momentum dump amount according to a predetermined dump cycle. That is, the dump cycle, the momentum dump amount, and the like are predetermined or previously measured based on such a normal operation, and thus, known. In this state, for example, when the situations in which there is a need to perform satellite missions for a time longer than <NUM> dump cycle, it is necessary to reduce the burden on the reaction wheel, or the like occur, the offset application request step is performed so that the satellite is ready to apply the offset.

In the offset momentum dump step, the momentum as much as the predetermined offset dump amount is dumped from the reaction wheel to generate the momentum offset in a direction opposite to the direction in which the momentum is accumulated. In this case, the offset dump amount is determined as a value smaller than the momentum dump amount. In normal operation, when the momentum is dumped after <NUM> dump cycle, the accumulated momentum becomes <NUM>, whereas when the offset momentum dump step is performed, the momentum offset is generated in the direction opposite to the direction in which the momentum is accumulated. For example, in the first embodiment described above, as the momentum offset, momentum for <NUM> hours is generated, and in the second embodiment, momentum for <NUM> hours is generated.

First, when the momentum dump method of the present disclosure is applied to a satellite that intends to go into orbit and start operation during the first operation of the satellite, a step of making the momentum stored in the reaction wheel become <NUM> by performing initial setting to start the operation of the satellite on the orbit, the offset application request step, and the offset momentum dump step may be sequentially performed. By doing so, the momentum offset has been already generated in the reaction wheel in the first state, and in this state, the satellite may be operated to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle.

In the above simple example, conventionally, when the momentum accumulated in the reaction wheel for <NUM> dump cycle is <NUM>, it is described that a momentum of [<NUM> to <NUM>] is stored in the reaction wheel while an operating time is [<NUM> to <NUM> dump cycle]. In this case, in the present disclosure, the momentum already stored in the reaction wheel in the initial state may be -<NUM> (by the momentum offset) due to the execution of the steps as described above. Then, the satellite to which the momentum dump method of the present disclosure is applied may be operated so that the momentum of [-<NUM> to <NUM>] is stored in the reaction wheel while the operating time is [<NUM> to <NUM> dump cycle] from the beginning.

Alternatively, when the momentum dump method of the present disclosure is applied to the satellite in the normal operation of the satellite, that is, the operation to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle, the offset application request step, a step in which <NUM> dump cycle being performed at a time when the offset application request step is performed is completed, and thus, the momentum as much as the momentum dump amount is dumped from the reaction wheel so that the stored momentum becomes <NUM>, and the offset momentum dump step may be sequentially performed. By doing so, the momentum offset has been already generated in the reaction wheel immediately before the next <NUM> dump cycle starts, and in this state, the satellite is operated to dump the momentum as much as the known momentum dump amount according to the predetermined dump cycle.

According to the original normal operation, the accumulated momentum of [<NUM> to <NUM>] is generated in the reaction wheel while the operating time is [<NUM> to <NUM> dump cycle], so the storage momentum of the reaction wheel becomes <NUM> immediately after <NUM> dump cycle. However, in this case, the momentum offset is generated immediately, so the storage momentum of the reaction wheel may be -<NUM> immediately before the next <NUM> dump cycle starts. Then, the satellite to which the momentum dump method of the present disclosure is applied may be operated so that the momentum of [-<NUM> to <NUM>] is stored in the reaction wheel while the operating time is [<NUM> to <NUM> dump cycle] after the offset application request step.

In this way, when the offset momentum dump step is performed, since a sufficient momentum offset is generated, the long-term satellite mission performance step in which the satellite mission is performed without momentum dump for <NUM> dump cycle or longer time may be performed. Specifically describing, by generating the momentum offset in this way, the satellite mission may be performed for a time period of <NUM> dump cycle or more, and the amount of momentum stored in the reaction wheel may be significantly reduced compared to the conventional one, even if the satellite mission is performed only for one dump cycle time as before in terms of time.

As a specific example, in the case of the first embodiment, when <NUM> dump cycle is <NUM> hours and the long-term satellite mission performance period is <NUM> hours, the momentum offset may be determined as a value corresponding to the accumulated momentum amount due to solar radiation pressure for a <NUM>/<NUM> long-term satellite mission performance period, that is, <NUM> hours. In this case, since the operation itself in which the momentum dump is generated is the same as in the related art, it can be seen that it is operated as in the related art in terms of time, but as confirmed by the storage momentum graphs of <FIG> (conventional) and <NUM> (first embodiment), the amount of momentum stored in the reaction wheel significantly decreases, which significantly reduces the load on the reaction wheel.

As a specific example, in the case of the second embodiment, when <NUM> dump cycle is <NUM> hours and the long-term satellite mission performance period is <NUM> hours, the momentum offset may be determined as a value corresponding to the accumulated momentum amount due to solar radiation pressure for a <NUM>/<NUM> long-term satellite mission performance period, that is, <NUM> hours. In this case, the long-term satellite mission performance step may be more reliably continued for a longer period of time compared to the related art, and when viewed from the storage momentum graphs of <FIG> (conventional) and <FIG> (second embodiment), it is confirmed that, after <NUM> hours of operation without momentum dump for a longer period of time, the stored amount of momentum is much smaller than before.

As confirmed in the first and second embodiments, the stored amount of momentum after <NUM> dump cycle (<NUM> hours in the case of the embodiments) has elapsed is naturally smaller than the accumulated amount of momentum of <NUM> dump cycle during normal operation, and the stored amount of momentum after a longer period of time (for example, <NUM> hours) than <NUM> dump cycle is naturally smaller than the accumulated amount of momentum during the same time during the normal operation, and smaller than the accumulated amount of momentum for <NUM> dump cycle during the normal operation. As the stored amount of momentum increases, the momentum capacity of the reaction wheel needs to be large enough to smoothly digest the increasing momentum. However, by using the present disclosure, for example, even with the reaction wheel having the momentum capacity sufficient to store the accumulated amount of momentum for <NUM> hours, even if the momentum is accumulated for <NUM> hours by applying the offset to the momentum dump as described above, since the actual stored amount is less than the accumulated momentum for <NUM> hours during the normal operation, the momentum dump may be performed smoothly without any problems such as straining the reaction wheel. In other words, the momentum capacity requirements of the reaction wheel may be greatly alleviated.

The present disclosure is not limited to the abovementioned exemplary embodiments, but may be variously applied. In addition, the present disclosure may be variously modified by those skilled in the art to which the present disclosure pertains without departing from the scope of the present invention defined in the claims.

Claim 1:
A momentum dump method for a satellite reaction wheel operated to dump momentum as much as a known momentum dump amount according to a predetermined dump cycle, characterised in that the momentum dump method comprises:
a momentum offset application requesting step in which a momentum offset application is requested during the momentum dump to the satellite; and
an offset momentum dumping step in which the momentum as much as a predetermined momentum offset dump amount is dumped from the reaction wheel to generate a momentum offset in a direction opposite to a direction in which the momentum is accumulated, wherein
the predetermined momentum offset dump amount is determined within a range of greater or equal <NUM>% to less than <NUM>% of the moment dump amount.