KR20170068127A - A satellite with a breaking system using eddy current - Google Patents

A satellite with a breaking system using eddy current Download PDF

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Publication number
KR20170068127A
KR20170068127A KR1020150174972A KR20150174972A KR20170068127A KR 20170068127 A KR20170068127 A KR 20170068127A KR 1020150174972 A KR1020150174972 A KR 1020150174972A KR 20150174972 A KR20150174972 A KR 20150174972A KR 20170068127 A KR20170068127 A KR 20170068127A
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KR
South Korea
Prior art keywords
eddy current
satellite
control unit
generating unit
magnitude
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KR1020150174972A
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Korean (ko)
Inventor
서현호
김대관
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한국항공우주연구원
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Priority to KR1020150174972A priority Critical patent/KR20170068127A/en
Publication of KR20170068127A publication Critical patent/KR20170068127A/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/02—Details of the space or ground control segments
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K49/00—Dynamo-electric clutches; Dynamo-electric brakes
    • H02K49/02—Dynamo-electric clutches; Dynamo-electric brakes of the asynchronous induction type
    • H02K49/04—Dynamo-electric clutches; Dynamo-electric brakes of the asynchronous induction type of the eddy-current hysteresis type

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Power Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Critical Care (AREA)
  • Emergency Medicine (AREA)
  • General Health & Medical Sciences (AREA)
  • Astronomy & Astrophysics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

There is provided a satellite for controlling an eddy current generated in the object by using an eddy current generating unit for sensing an object and including a magnetic body. Wherein the satellite includes a sensing unit sensing a moving object, an eddy current generating unit generating a eddy current in the object using the magnetic body, and a controller connected to the eddy current generating unit to control a distance to the object, And a control unit for controlling the magnitude and direction of the eddy current.

Description

A SATELLITE WITH A BREAKING SYSTEM USING EDDY CURRENT,

Relates to a satellite including a braking system, and more particularly to a satellite including a braking system for braking a rotating or translating object.

It is expected that at least 100 satellites will be fired annually from now on when the number of satellites launched worldwide has exceeded about 7,000. In these situations, it is expected that collision of space debris such as broken satellites, missed satellites, and peeling paint from rockets or space shuttles is expected to increase.

There are various technologies that use robot satellites, lasers, brushes, tethers, etc. to remove space debris. However, since most of the space debris is translational and rotational, it can generate momentum due to the reaction to other satellites during the removal process. Depending on the reaction, the orbits of other satellites can be modified to make precise control difficult.

According to one aspect of the present invention, there is provided a satellite for sensing an object and controlling an eddy current generated in the object by using an eddy current generating unit including a magnetic body. Wherein the satellite includes a sensing unit sensing a moving object, an eddy current generating unit generating a eddy current in the object using the magnetic body, and a controller connected to the eddy current generating unit to control a distance to the object, And a control unit for controlling the magnitude and direction of the eddy current.

According to an embodiment, the controller may decelerate the motion of the object by controlling the magnitude and direction of the eddy current.

According to another embodiment, the eddy current generating unit may include at least one of an electromagnet and a permanent magnet as the magnetic body, and the amount of magnetic flux change of the object may be adjusted using the electromagnet.

According to another embodiment, the satellite may further include a reaction wheel for canceling a reaction torque corresponding to the eddy current generated in the object.

According to another embodiment, the satellites may further include a magnetic talker for generating magnetic moments of the satellites according to the magnitude and direction of the geomagnetic field to cancel the reaction torque corresponding to the eddy current, And a geomagnetic sensor for sensing the magnitude and direction of the geomagnetic field.

According to another embodiment, the apparatus may further include a thruster for canceling a reaction force corresponding to the eddy current generated in the object.

According to another embodiment, the sensing unit may include a camera for sensing image data representing a direction of motion of the object, and the motion direction may include at least one of a translational motion direction and a rotational motion direction. The control unit may control the satellite so that the distance to the object is reduced according to the direction of translation. The control unit may control the satellite so that the rotation axis of the object and the eddy current generating unit approach in a direction orthogonal to the rotation direction of the object.

According to another aspect, there is provided a braking system for a satellite including a first control unit for controlling translational motion of an object and a second control unit for controlling rotational motion of the object. A braking system of the satellites includes an eddy current generating unit that includes a magnetic body and generates an eddy current to the object using the magnetic body, a control unit that controls the magnitude and direction of the eddy current by controlling a distance between the eddy current generating unit and the object, And a second controller for controlling the magnitude and direction of the eddy current by controlling an angle between the first control unit, the eddy current generating unit, and the first rotating shaft of the object.

According to one embodiment, the first control unit includes at least one of a boom and a tether connected to one side of the eddy current generating unit, and the length of at least one of the boom and the tether is controlled So that the magnitude and direction of the eddy current can be controlled.

According to another embodiment, the second control unit includes a second rotation axis for rotating the eddy current generating unit, and the braking system of the satellite uses the second rotation axis to rotate the eddy current generating unit and the first rotation axis of the object It is possible to control the angle formed. In addition, the second rotation axis of the second control unit may be disposed in at least one of the boom and the tether of the first control unit.

1 is an exemplary view showing a braking operation of a satellite according to an embodiment.
FIGS. 2A and 2B are diagrams illustrating an operation of a control unit of a satellite according to an exemplary embodiment of the present invention.
3A and 3B are diagrams illustrating an operation of a control unit of a satellite according to another embodiment of the present invention.
4 is a block diagram illustrating a satellites according to one embodiment.
5 is a block diagram illustrating a braking system for a satellite according to an embodiment.

Specific structural or functional descriptions of embodiments are set forth for illustration purposes only and may be embodied with various changes and modifications. Accordingly, the embodiments are not intended to be limited to the particular forms disclosed, and the scope of the disclosure includes changes, equivalents, or alternatives included in the technical idea.

The terms first or second, etc. may be used to describe various elements, but such terms should be interpreted solely for the purpose of distinguishing one element from another. For example, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.

It is to be understood that when an element is referred to as being "connected" to another element, it may be directly connected or connected to the other element, although other elements may be present in between.

The singular expressions include plural expressions unless the context clearly dictates otherwise. In this specification, the terms "comprises ", or" having ", and the like, are used to specify one or more of the described features, numbers, steps, operations, elements, But do not preclude the presence or addition of steps, operations, elements, parts, or combinations thereof.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art. Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the meaning of the context in the relevant art and, unless explicitly defined herein, are to be interpreted as ideal or overly formal Do not.

1 is an exemplary view showing a braking operation of a satellite according to an embodiment. Referring to FIG. 1, a satellite 110 and an object 120 in an outer space are shown. Illustratively, the object 120 may be an object, such as a piece of space debris, meteorites, asteroids, and missiles that are debris of the satellites 110 and a portion of the satellites 110 falling to the ground, . Considering that a single satellite 110 is manufactured and launched and the investment cost for maintaining the mission is considerable, the failure or path deviation of the satellite 110 due to the collision with the object 120 causes a great loss in the nation This can be a problem.

Since the magnitude of the external force or the external torque is negligibly small, the object 120 flying in space can act as an external force or an external torque, It can be modeled as a moving object.

The satellites 110 may include a braking system for decelerating the object 120. More specifically, the satellite 110 decelerates the speed of the object 120 to prevent collision with the satellite 110, and the altitude of the object 120 can be lowered.

The satellites 110 may sense objects 120 flying in space. In addition, the satellite 110 can adjust its own trajectory in accordance with the trajectory motion of the object 120. In addition, the satellites 110 may include a controller 111 and an eddy current generator 112 for efficiently decelerating the object 120.

In the present specification, eddy current refers to a current generated in a direction to resist a change of the magnetic field when a magnetic field inside the conductor is abruptly changed, and may be referred to as an eddy current or a Foucault current.

The satellite 110 can control the distance and direction between the eddy current generator 112 and the object 120 by using the controller 111. [ The satellite 110 may generate an eddy current in the object 120 by using an eddy current generating unit 112 including a magnetic body. According to one embodiment, the object 120 may be subjected to a force in a direction opposite to the direction of translational motion according to the eddy current, so that the speed may be reduced. According to another embodiment, the object 120 may be stopped from rotating in accordance with the eddy current. A more detailed explanation for the satellites 110 to control the object 120 can be further explained together with the drawings added below.

FIGS. 2A and 2B are diagrams illustrating an operation of a control unit of a satellite according to an exemplary embodiment of the present invention. Referring to FIG. 2A, a satellite 210 and an object 220 in an outer space are shown. In addition, the satellite 210 may include a control unit 211 for controlling the distance that the eddy current generating unit 212 and the eddy current generating unit 212 extend from the satellite 210. In one embodiment, the eddy current generating unit 212 may be a permanent magnet, which is a permanent magnet and does not change permanently. In another embodiment, the eddy current generating portion 212 may be an electromagnet, which is magnetized when an electric current flows and returns to an original state that is not magnetized when the electric current is interrupted. 2A, the distance between the eddy current generator 212 and the object 220 of the satellites 210 may be defined as d 1 . Further, the magnetic flux passing through the surface of the object 220 from the eddy current generating section 212 becomes " 1 < / RTI >

The satellite 210 can sense the object 220 existing within the critical distance. In addition, the satellite 210 can detect the moving speed and the moving direction of the object 220. According to the movement speed, the satellite body 210 can approach the eddy current generator 212 to the object 220 within a range where the satellite body 210 does not collide. More specifically, the satellites 210 can access the eddy current generator 212 to the object 220 by using the controller 211.

Referring to FIG. 2B, the distance between the eddy current generating unit 212 of the satellite 210 and the object 220 is changed to d 2 . Illustratively, d 2 may be less than d 1 , and the distance between the eddy current generator 212 and the object 220 may be reduced. In the case of FIG. 2B, the magnetic flux passing through the surface of the object 220 from the eddy current generating portion 221 is? 2 < / RTI > More specifically, ??? 2 is the ?? 1 , the amount of change of the magnetic flux passing through the surface of the object 220 can be increased.

Thereby, an electromotive force can be generated on the surface of the object 220 in a direction which hinders the increase of the magnetic flux. Depending on the electromotive force, the object 220 may be subjected to a force in a direction in which the velocity of the current translational motion is decelerated. In addition, the object 220 can not maintain the current altitude according to the received force, and the altitude can be reduced according to the earth's gravity.

The satellites 210 can generate an eddy current in a direction that interferes with the translational motion of the object 220 by using the control unit 211 and the eddy current generating unit 212 as described above. According to the generated eddy current, the speed of translational movement of the object 220 can be reduced. The satellites 210 reduce the possibility of collision with the object 220 and can more reliably use the Debris Removal System. In addition, the satellites 210 may have an opportunity to remove more objects 220 while lowering their altitudes, and the method of lowering and operating the altitudes of the satellites 210 may be performed by changing the altitude of the satellites 210 It is possible to expect the effect of effectively using the satellite 210 more effectively.

In this embodiment, the contents of the magnetic flux according to the distance between the satellite 210 and the object 220, the generation of the electromotive force according to the amount of change of the magnetic flux, and the generation direction of the electromotive force are described by Gauss's law, Lenz's law and Faraday's law, which are straight forward to those skilled in the art, and will not be described in detail herein.

3A and 3B are diagrams illustrating an operation of a control unit of a satellite according to another embodiment of the present invention. Referring to FIG. 3A, a satellite 310 and an object 320 existing in an outer space are shown. In the embodiment of FIG. 3A, the object 320 may be modeled as rotating motion along any rotational axis 321 as well as translational motion. 2A, the satellite unit 310 may include an eddy current generating unit 312. [ 3A, the satellite 310 may include a control unit 311 for controlling an angle formed by the approach direction of the eddy current generating unit 312 with the rotation axis 321 of the object 320. In this case, 3A, the angle formed by the approach direction of the eddy current generator 312 of the satellite 310 and the rotation axis 321 of the object 320 can be defined as? 1 .

3B, the angle formed by the approach direction of the eddy current generator 312 and the rotation axis 321 of the object 320 may be changed to? 2 . By way of example, &thetas; 2 may represent 90 degrees. The satellites 310 can rotate the eddy current generating unit 312 around the control unit 311. Accordingly, the angle formed by the approach direction of the eddy current generating portion 312 with the rotation axis 321 of the object 320 can be changed from? 1 to? 2 . Illustratively, the control unit 311 may be implemented as a robot apparatus having a rotating joint. In addition, the earth station can transmit a telecommand related to the operation of the control unit 311 to the satellite unit 310, and the satellite unit 310 can operate the control unit 311 according to the received remote command.

The satellite body 310 can change the direction of change of the magnetic flux generated by the eddy current generator 312 of the satellite body 310 by using the controller 311. [ In other words, the satellite body 310 can increase the magnetic flux in the surface of the object 320 in a direction orthogonal to any arbitrary rotation axis 321 of the object 320. Accordingly, the satellite body 310 can stop the rotational motion of the object 320 more efficiently.

4 is a block diagram illustrating a satellites according to one embodiment. 4, the satellite 400 may include a sensing unit 410, an eddy current generator 420, a controller 430, a reaction wheel 440, a magnetic talker 450, and a thruster 460 . The sensing unit 410 may sense an object to be moved. More specifically, the sensing unit 410 can sense a plurality of objects existing at a lower altitude than the satellites 400. Illustratively, the object may be a rotating or translating object. More specifically, the sensing unit 410 may include a camera for sensing image data representing a direction of motion of the object. In one embodiment, the sensing unit 410 may be implemented as a charge coupled device (CCD) camera that converts an image into an electrical signal using a charge coupled device and acquires image data in the form of digital data. In another embodiment, the sensing unit 410 may be implemented as a thermal imaging infrared camera that senses electromagnetic radiation within a wavelength band of 0.9 μm or more and 14 μm or less and acquires a sensed image. For example, the sensing unit 410 may sense motion direction and motion velocity of the object by comparing a plurality of image data corresponding to each of the plurality of viewpoints having a predetermined time interval.

The eddy current generating part 420 may include a magnetic body. More specifically, the eddy current generating unit 420 may include at least one of the electromagnet and the permanent magnet as the magnetic body. The eddy current generating unit 420 can generate an eddy current in the object using the magnetic body. In one embodiment, the eddy current generating unit 420 may control a current flowing along the electromagnet to control a magnetic flux variation of the object.

The control unit 430 is connected to the eddy current generating unit 420 and controls the distance and direction between the eddy current generating unit 420 and the objects and controls the magnitude and direction of the eddy current generated in the object. Illustratively, when the eddy current generator 420 includes an electromagnet, a current must be applied to the electromagnet to generate an eddy current in the object.

However, when the distance between the eddy current generating unit 420 and the main body of the satellite 400 is within a predetermined critical distance, the magnetic field generated by the electromagnet may affect not only the object but also the satellite 400 have. In such a case, it may become difficult to carry out and control the mission of the satellite 400 itself due to the magnetic field generated by the eddy current generator 420 inside the satellite 400. Accordingly, the control unit 430 can make the eddy current generator 420 move away from the body of the satellite 400 by a critical distance. More specifically, the critical distance may indicate a distance at which the magnetic field generated by the eddy current generating unit 420 does not affect the satellite 400. In addition, the control unit 430 may decelerate the movement of the object by controlling the magnitude and direction of the eddy current. In addition, the control unit 430 may sequentially decelerate the motion of the plurality of objects detected according to the altitude corresponding to the plurality of objects.

The reaction wheel 440 may cancel the reaction torque corresponding to the eddy current generated in the object. More specifically, the reaction wheel 440 may include an electric motor and a rotor. The satellite 400 can rotate the rotating body using the electric motor and generate a rotational force in a direction canceling the reaction torque transmitted from the object. Accordingly, the reaction torque transmitted to the satellite 400 can be canceled by the reaction wheel 440, and the satellite 400 can maintain the flight attitude corresponding to the mission plan.

The magnetic torquer 450 may generate a magnetic moment of the satellite 400 to cancel the reaction torque corresponding to the eddy current. More specifically, the magnetic talker 450 can generate the magnetic moment of the satellite 400 according to the magnitude and direction of the earth's magnetic field. The sensing unit 410 may further include a geomagnetic sensor for sensing the magnitude and direction of the geomagnetic field. Illustratively, the magnetic talker 450 may be implemented in the form of a coil or rod that includes a conductor. More specifically, the coil may be in the form of being wound with a conductor wire. The magnetic talker 450 may generate a rotational force in a direction canceling the reaction torque transmitted from the object by using the interaction between the magnetic field generated by flowing current through the coil or the rod and the earth's magnetic field.

The thruster 460 may cancel at least one of the reaction force and the reaction torque corresponding to the eddy current generated in the object. In one embodiment, the thruster 460 may be embodied as a gas jet thruster that emits fuel contained in the satellite 400 in the form of a gas jet, and obtains a force in response to a reaction corresponding to the emission. In addition, the thruster 460 may utilize a momentum arm to obtain torque in response to a reaction corresponding to the release. In another embodiment, the thruster 460 may be implemented as a small thruster generating a fine-sized thrust. In addition, it can be implemented in various forms such as a hydrazine thruster, an ion thruster, a pulse plasma thruster, and a hall thruster used as a thruster 460 of a satellite 400 today.

4, an embodiment including both a reaction wheel 440, a magnetic talker 450, and a thruster 460 is shown, but this is merely an example description to help understand the concept of the present invention Only. In addition, the above description does not limit or limit the scope of rights. Therefore, it is also within the scope of the present invention to implement the satellite 400 using at least one of the above constructions to offset the reaction force and the reaction torque corresponding to the eddy currents.

5 is a block diagram illustrating a braking system for a satellite according to an embodiment. 5, the satellite braking system 500 may include an eddy current generator 510, a first controller 520, and a second controller 530. The eddy current generating part 510 includes a magnetic body, and the eddy current can be generated in the object using the magnetic body. In addition, the detailed description of the eddy current generating unit 510 will be omitted because the explanation of the eddy current generating unit 420 described in FIG. 4 can be applied as it is.

The first controller 520 controls the magnitude and direction of the eddy current generated by controlling the distance between the eddy current generator 510 and the object. More specifically, the first control unit 520 may be connected to one side of the eddy current generating unit 510. Also, the first control unit 520 may include at least one of a boom and a tether, and may control the length and / or the direction of the eddy current by controlling the length of at least one of the boom and the tether in an outer space . The boom may be implemented in the form of a rigid body having a certain volume to indicate a rod connected to the eddy current generating part 510. The tether may have a tension greater than a threshold value and may indicate a tether connected to the eddy current generator 510.

In addition, the second control unit 530 may include a second rotation axis for rotating the eddy current generating unit 510. The second controller 530 may control the angle formed by the eddy current generator 510 and the first rotation axis of the object using the second rotation axis. The first rotation axis may indicate a rotation axis corresponding to the rotation motion of the object. In one embodiment, the second rotation axis may be embodied as a robot apparatus including a revolute joint. The robot apparatus may receive a control signal from a satellite and rotate the eddy current generator 510 to correspond to the control signal. The second rotation axis of the second control unit 530 may be disposed in at least one of the boom and the tether of the first control unit 520.

According to the present embodiment, the braking system 500 of the satellite may include a first control unit 520 and a second control unit 530. The first control unit 520 for adjusting the distance of the object and the second control unit 530 for adjusting the angle between the rotation axis of the object and the braking system 500 of the satellite simultaneously implement the braking system 500 Can be expected to simultaneously decelerate the translational motion and the rotational motion of the object even when the eddy current generator 510 is included. However, this is merely an explanatory drawing of the effect according to the present embodiment, and it should not be construed as excluding or limiting the case where at least two eddy current generators 510 are included in the scope of the present invention.

The embodiments described above may be implemented in hardware components, software components, and / or a combination of hardware components and software components. For example, the devices, methods, and components described in the embodiments may be implemented within a computer system, such as, for example, a processor, a controller, an arithmetic logic unit (ALU), a digital signal processor, such as an array, a programmable logic unit (PLU), a microprocessor, or any other device capable of executing and responding to instructions. The processing device may execute an operating system (OS) and one or more software applications running on the operating system. The processing device may also access, store, manipulate, process, and generate data in response to execution of the software. For ease of understanding, the processing apparatus may be described as being used singly, but those skilled in the art will recognize that the processing apparatus may have a plurality of processing elements and / As shown in FIG. For example, the processing unit may comprise a plurality of processors or one processor and one controller. Other processing configurations are also possible, such as a parallel processor.

The software may include a computer program, code, instructions, or a combination of one or more of the foregoing, and may be configured to configure the processing device to operate as desired or to process it collectively or collectively Device can be commanded. The software and / or data may be in the form of any type of machine, component, physical device, virtual equipment, computer storage media, or device , Or may be permanently or temporarily embodied in a transmitted signal wave. The software may be distributed over a networked computer system and stored or executed in a distributed manner. The software and data may be stored on one or more computer readable recording media.

The method according to an embodiment may be implemented in the form of a program command that can be executed through various computer means and recorded in a computer-readable medium. The computer-readable medium may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions to be recorded on the medium may be those specially designed and configured for the embodiments or may be available to those skilled in the art of computer software. Examples of computer-readable media include magnetic media such as hard disks, floppy disks and magnetic tape; optical media such as CD-ROMs and DVDs; magnetic media such as floppy disks; Magneto-optical media, and hardware devices specifically configured to store and execute program instructions such as ROM, RAM, flash memory, and the like. Examples of program instructions include machine language code such as those produced by a compiler, as well as high-level language code that can be executed by a computer using an interpreter or the like. The hardware devices described above may be configured to operate as one or more software modules to perform the operations of the embodiments, and vice versa.

Although the embodiments have been described with reference to the drawings, various technical modifications and variations may be applied to those skilled in the art. For example, it is to be understood that the techniques described may be performed in a different order than the described methods, and / or that components of the described systems, structures, devices, circuits, Lt; / RTI > or equivalents, even if it is replaced or replaced.

Claims (14)

A sensing unit for sensing an object to be moved;
An eddy current generator including a magnetic body and generating an eddy current in the object using the magnetic body; And
A control unit connected to the eddy current generating unit and controlling the magnitude and direction of the eddy current by controlling a distance to the object,
. The method according to claim 1,
Wherein the control unit controls the magnitude and direction of the eddy current to decelerate the motion of the object. The method according to claim 1,
Wherein the eddy current generating unit includes at least one of an electromagnet and a permanent magnet as the magnetic body, and adjusts a magnetic flux change amount of the object using the electromagnet. The method according to claim 1,
A reaction wheel for canceling a reaction torque corresponding to the eddy current generated in the object;
. 5. The method of claim 4,
The magnetic torque of the satellites is generated according to the magnitude and direction of the earth's magnetic field to cancel the reaction torque corresponding to the eddy current,
Further comprising:
Wherein the sensing unit includes a geomagnetic sensor for sensing magnitude and direction of a geomagnetic field. The method according to claim 1,
A thruster for canceling a reaction force corresponding to the eddy current generated in the object
. The method according to claim 1,
Wherein the sensing unit includes a camera for sensing image data representing a direction of motion of the object, and the motion direction includes at least one of a translational motion direction and a rotational motion direction. 8. The method of claim 7,
Wherein the control unit controls the satellite so that the distance to the object decreases in accordance with the translational motion direction. 8. The method of claim 7,
Wherein the control unit controls the satellite so that the rotation axis of the object and the eddy current generating unit approach in a direction perpendicular to the rotation direction of the object. The method according to claim 1,
Wherein the sensing unit senses at least one object existing at a lower altitude than the satellite and the control unit sequentially controls the magnitude and direction of the eddy current according to the altitude at which the at least one object exists. An eddy current generator including a magnetic body and generating an eddy current in the object using the magnetic body;
A first controller for controlling the magnitude and direction of the eddy current by controlling a distance between the eddy current generating unit and the object; And
A second controller for controlling the magnitude and direction of the eddy current by controlling the angle formed by the eddy current generating unit and the first rotation axis of the object,
The braking system comprising: 12. The method of claim 11,
Wherein the first control unit includes at least one of a boom and a tether connected to one side of the eddy current generating unit and controls the length of at least one of the boom and the tether in an outer space, A braking system for a satellite that controls direction. 13. The method of claim 12,
Wherein the second control unit includes a second rotation axis for rotating the eddy current generating unit and controls an angle formed by the eddy current generating unit and the first rotation axis of the object using the second rotation axis. 14. The method of claim 13,
And the second rotation axis of the second control unit is disposed in at least one of the boom and the tether of the first control unit.
KR1020150174972A 2015-12-09 2015-12-09 A satellite with a breaking system using eddy current KR20170068127A (en)

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