System and method for controlling a target satellite

Abstract

An exemplary system for controlling a target satellite includes a satellite control spacecraft including a propulsion subsystem configured to propel and navigate the spacecraft in proximity to the target satellite, and a satellite capture subsystem configured to capture the target satellite, apply a control medium to the target satellite, and release the target satellite, the control medium comprising a conductive and / or magnetic material, and an energy supply assembly configured to energize the control medium to release energy to control, propel, and navigate the target satellite.

Description

[Technical field]

[0001] FIELD OF THE DISCLOSURE This disclosure relates generally to systems for operations in space, and more particularly to systems and methods for controlling and providing maneuverability to a target satellite in space. [Background technology]

[0002] Satellites generally orbit the Earth in regularly repeating orbits. Once in orbit, satellites tend to maintain their flight path. When a satellite has completed its purpose or run out of fuel, it is often retired to a higher orbit, leaving it in orbit as useless junk or debris. As such debris accumulates, it increases the likelihood of collisions with other satellites, used rockets, or pieces of satellites, and in large quantities it can disrupt the functioning of active satellites. Summary of the Invention [Means for solving the problem]

[0003] According to one aspect of the present disclosure, there is provided a system for controlling a target satellite, the system including a satellite control spacecraft including a propulsion subsystem configured to propel and navigate the spacecraft in proximity to the target satellite, and a satellite capture subsystem configured to capture the target satellite, apply a control medium to the target satellite, and release the target satellite, the control medium comprising a conductive and / or magnetic material, and an energy supply assembly configured to energize the control medium to release energy to control the target satellite.

[0004] According to another aspect of the present disclosure, there is provided a method for controlling a target satellite, the method including the steps of capturing the target satellite by a satellite control spacecraft, applying a control medium to the target satellite by the satellite control spacecraft, the control medium including a conductive material and / or a magnetic material, releasing the target satellite by the satellite control spacecraft, and energizing the control medium by an energy supply assembly to release energy for controlling the target satellite.

[0005] According to another aspect of the present disclosure, there is provided another method of controlling a target satellite, the method including pre-applying a control medium to the target satellite, launching the target satellite, and energizing the control medium by an energy supply assembly to release energy for controlling the target satellite. [Brief description of the drawings]

[0006] The embodiments are described with reference to the following figures:

[0007] [Figure 1] FIG. 1 shows a schematic diagram of a spacecraft for controlling a target satellite in space and for providing maneuverability to the target satellite. [Diagram 2] FIG. 2 is a schematic diagram showing a state in which the satellite capture subsystem in the system of FIG. 1 has captured a target satellite. [Diagram 3] FIG. 3 shows a schematic diagram of the satellite capture subsystem attaching the auxiliary module to the target satellite. [Figure 4] FIG. 4 shows a schematic diagram of a spacecraft energy supply assembly for satellite control supplying energy to conductive and / or magnetic materials of an auxiliary module. [Diagram 5] FIG. 5 shows a schematic diagram of the energy delivery assembly of the auxiliary module energizing the conductive and / or magnetic materials. [Figure 6] FIG. 6 shows a schematic diagram of the satellite capture system applying dispersed particulate matter to a target satellite. [Figure 7] FIG. 7 shows a schematic diagram of a remote energy delivery assembly for remotely energizing conductive and / or magnetic materials. [Figure 8] FIG. 8 shows a schematic diagram of the control path of the target satellite. [Figure 9] FIG. 9 illustrates a method for controlling a target satellite in space and providing maneuverability to the target satellite. [Figure 10] FIG. 10 illustrates a method for applying the control medium to a target satellite. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0008] The present disclosure provides systems and methods for controlling and providing mobility to a target satellite in space. In particular, the systems and methods disclosed herein enable missions and / or positioning of other satellites in orbit, including debris removal, orbital maneuvers, gaining control of uncontrolled objects, sticking satellites and / or satellite fragments together, and controlling the attitude of the spacecraft. Specifically, conductive and / or magnetic materials, such as reactive metal compounds in different combinations and spatial configurations, may be applied to the target satellite in the form of a control medium. The conductive and / or magnetic materials may then be combusted and / or sintered remotely, for example, by induction or via solar, laser, microwave energy, or other electromagnetic radiation. The ignition profile of the control medium may be specifically selected such that upon ignition, the target satellite is controlled in a specific manner, for example, to de-orbit the target satellite, move the target satellite to a pre-designated area, bind to other satellites and / or objects, or change the orbit of the target satellite.

[0009] FIG. 1 illustrates an exemplary system 100 for controlling a target satellite 102 in space. The target satellite 102 may be, for example, an active satellite (e.g., for monitoring, data capture, etc.), debris, or other object in orbit. The system 100 includes a satellite control spacecraft 110. The satellite control spacecraft 110 (also referred to herein simply as the spacecraft 110) is generally configured to perform control operations for controlling the target satellite 102. For example, the control operations may be to change the orbit of the target satellite 102, to de-orbit the target satellite 102, or to move the target satellite 102 to a pre-designated area. The spacecraft 110 may include metals, metal alloys, composite materials, etc. suitable for housing and protecting the internal components of the spacecraft 110 in space.

[0010] Spacecraft 110 includes a propulsion subsystem 112 configured to propel and navigate the spacecraft in proximity to target satellite 102. For example, propulsion subsystem 112 may include propulsion components, such as, but not limited to, engines, rockets, motors, etc., for propelling spacecraft 110. Propulsion subsystem 112 may also include navigation components, such as sensors, beacons, localization modules, etc., for navigating spacecraft 110 in space. Additionally, propulsion subsystem 112 may include a controller that controls the propulsion components, navigation components, and any other components of propulsion subsystem 112.

[0011] The propulsion subsystem 112 is generally configured to detect the target satellite 102 and direct the spacecraft in proximity to the target satellite. For example, the navigation component may detect the target satellite 102 (e.g., with a sensor, etc.) and generate navigation data. The propulsion component, when controlled by, for example, a controller, may propel and navigate the spacecraft 110 in proximity to the target satellite 102 according to the navigation data.

[0012] The spacecraft 110 further includes a satellite capture subsystem 114 configured to selectively capture (grab) and release the target satellite 102. The satellite capture subsystem 114 includes one or more capture components, such as, but not limited to, one or more robotic arms, claws, tethers, etc., for capturing the target satellite 102. In other examples, the satellite capture subsystem 114 may further include one or more magnetic components configured to capture the target satellite 102 and hold the target satellite 102 in place during control operations. Other suitable capture components are contemplated.

[0013] The satellite capture subsystem 114 further includes a control medium applicator configured to apply a control medium 116 to the target satellite 102. The control medium 116 includes a conductive material and / or a magnetic material. The conductive material and / or the magnetic material can be, for example, a reactive metal compound such as a nanothermite or a microthermite. In particular, the nanothermite or microthermite includes an oxidizer and a reducer (e.g., a metal and a metal oxide). The nanothermite or microthermite is configured to be ignited and / or energized by induction, for example, to induce eddy currents and / or hysteresis in the nanothermite or microthermite, which induces a reaction between them, thereby releasing energy. In other examples, the nanothermite or microthermite may be ignited by other sources, such as a laser beam, a microwave beam, sunlight, or other electromagnetic radiation. More generally, the conductive material and / or the magnetic material can include solids and / or various types of fluids (including liquids, gases, combinations, etc.) that include conductive particles or components.

[0014] The conductive particles or components can be energized (energized) and / or ignited to heat the control medium 116 to control the target satellite 102. Thus, the particular components of the conductive and / or magnetic materials may be selected to react and ignite below the Curie temperature of the material. Thus, the conductive and / or magnetic materials may be energized to their reaction ignition point to combust and / or sinter the conductive and / or magnetic materials. For example, the conductive and / or magnetic materials may include reactive metal compounds, compounds in a gaseous state, compounds in a liquid state, compounds in a solid state, slurries of materials with multiple phases or states, synthetic and non-synthetic polymers, and the like. The conductive and / or magnetic materials may further include mixtures of layers of materials, multi-coated metals with metamaterials, hybrid mixtures of reactive metal compounds in a liquid state and an inert state, or other suitable combinations of materials.

[0015] 1, the control medium 116 can include an auxiliary module 117 having a layer 118 of conductive and / or magnetic material. The auxiliary module 117 can be configured to attach to the target satellite 102. In such examples, the control medium applicator can be a robotic arm or the like that applies the auxiliary module 117 to the target satellite 102.

[0016] The system 100 further includes an energy supply assembly 120 configured to energize the control medium 116. In particular, the energy supply assembly is configured to energize the conductive and / or magnetic materials to release energy for controlling the target satellite 102. In some examples, the energy supply assembly 120 may be located within the spacecraft 110. In other examples, the energy supply assembly 120 may be located within the control medium 116 itself. In further examples, the energy supply assembly 120 may be located remotely from the system 100, such as on another spacecraft or on Earth.

[0017] In operation, the propulsion subsystem 112 is configured to steer the spacecraft 110 in proximity to the target satellite 102. For example, the propulsion subsystem 112 may use one or more sensors or detectors to orient the target satellite 102 and may use its engines to propel the spacecraft 110 toward the target satellite. The propulsion subsystem 112 may also steer the spacecraft 110 such that the satellite capture subsystem 114 is directed toward the target satellite 102.

[0018] When the spacecraft 110 is in position, the satellite capture subsystem 114 is configured to capture the target satellite 102. For example, with reference to Figure 2, the spacecraft 110 is depicted with the satellite capture subsystem 114 capturing the target satellite 102. The satellite capture subsystem 114 may use one or more of a robotic arm, a magnetic component, a tether system, a mesh, etc. to capture the target satellite 102.

[0019] After capturing the target satellite 102, the satellite capture subsystem 114 is configured to apply the control medium 116 to the target satellite 102. For example, referring to FIG. 3, the auxiliary module 117 is attached to the target satellite 102. For example, the satellite capture subsystem 114 may use one or more additional robotic arms to attach the auxiliary module 117 to the target satellite 102. The auxiliary module 117 may be attached to the target satellite 102 by one or more adhesives, such as those applied by the satellite capture subsystem 114 during application of the control medium 116 to the target satellite 102. In other examples, the adhesives may be pre-applied to the auxiliary module 117 and activated, for example, via contact with the target satellite 102 or by the satellite capture subsystem 114 during application of the control medium to the target satellite 102. In further examples, the auxiliary module 117 may be attached to the target satellite 102 via fasteners or other mechanical means.

[0020] In some examples, the satellite capture subsystem 114 may include an auxiliary module generator (not shown) configured to print or otherwise manufacture the auxiliary module 117. The auxiliary module generator may include one or more detection devices, such as an imaging device (e.g., color camera, IR camera, etc.), a depth sensor, a scanner, or other suitable device, to determine the shape of the target satellite 102 or the shape of a region of interest of the target satellite 102 to which the auxiliary module 117 is to be applied. The auxiliary module generator may generate a model of the target satellite or region of interest and a model of the auxiliary module that fits the target satellite or region of interest. The auxiliary module generator may also include a printer, such as a 3D printer, for printing the auxiliary module 117 according to the model. Thus, the auxiliary module 117 may be formed in a shape that fits the target satellite 102.

[0021] In other examples, the shape of the target satellite or satellite's area of ​​interest may be known, and auxiliary module 117 may be prefabricated (eg, prior to launch of spacecraft 100).

[0022] When the control medium 116 is applied to the target satellite 102, the satellite capture subsystem 114 is configured to release the target satellite 102 along with the control medium 116. The energy supply assembly 120 is then configured to energize the control medium 116, particularly the conductive and / or magnetic materials, to release energy for controlling the target satellite 102. For example, with reference to FIGURE 4, the energy supply assembly 120 may be disposed within the spacecraft 110 and may include an induction heating assembly 400.

[0023] The induction heating assembly 400 includes a coil 402 and a power supply circuit 404. In particular, the coil 402 is configured to be oriented adjacent to a conductive and / or magnetic material of the control medium 116. For example, the coil 402 is oriented adjacent to a layer 118 of a conductive and / or magnetic material of the auxiliary module 117. In particular, the propulsion subsystem 112 may be configured to move the spacecraft 110 such that the energy supply assembly 120 is aligned with the layer 118 of the auxiliary module 117. The power supply circuit 404 is configured to apply a current to the coil 402. For example, the power supply circuit 404 may be an oscillator circuit or other suitable circuit for passing a high frequency alternating current through the coil 402. In accordance with Ampere's law, the current flowing through the coil 402 induces a magnetic field 406 around the coil 402. In some implementations, the power supply circuit 404 is configured to vary the current passing through the coil 402, thereby varying the magnetic field 406. In other embodiments, the coil 402 may be configured to move (e.g., via a positioning mechanism or other mechanical means) to change the magnetic field 406. According to Faraday's law of induction, the changing magnetic field 406 induces eddy currents and / or hysteresis in nearby conductors, particularly the conductive and / or magnetic material layers 118. This eddy currents and / or hysteresis, in turn, energize and ignite the conductive and / or magnetic materials, thereby releasing energy to control the target satellite 102. Thus, the layers 118 may be configured to have specific ignition profiles (e.g., by using different conductive and / or magnetic materials in different combinations or spatial configurations) to enable specific control of the target satellite 102.

[0024] In further embodiments, the energy supply assembly need not be located within the spacecraft. For example, referring to FIG. 5, an exemplary target satellite 502 is depicted with an auxiliary module 517 attached thereto. The auxiliary module 517 includes a layer 518 of conductive and / or magnetic material. Additionally, an energy supply assembly is located on the auxiliary module 517. The energy supply assembly includes an induction heating assembly 520 that is similar to the induction heating assembly 400. The energy supply assembly may further include a processor or controller (not shown) that controls the operation of the induction heating assembly 520 and thus the energy supply of the conductive and / or magnetic material. The induction heating assembly 520 includes a coil 522 oriented adjacent to the layer 518 of conductive and / or magnetic material and a power supply circuit 524. The power supply circuit 524 is configured to pass a current through the coil 522, thereby inducing a magnetic field 526. In some implementations, power supply circuitry 524 may vary the current passing through coil 522, and in other implementations, coil 522 may move (e.g., parallel to the plane of layer 518) to vary magnetic field 526. The changing magnetic field 526 induces eddy currents in layer 518 of conductive and / or magnetic material, igniting the conductive and / or magnetic material, thereby releasing energy for controlling target satellite 502. Layer 518 may likewise be configured to have specific ignition profiles (e.g., by using different conductive and / or magnetic materials in different combinations or spatial configurations) to enable specific control of target satellite 502.

[0025] 6, an exemplary system 600 for controlling a target satellite is depicted. The system 600 is similar to the system 100 and includes a spacecraft 610 for satellite control including a propulsion subsystem 612 configured to propel and navigate the spacecraft 610, and a satellite capture subsystem 614 configured to selectively capture and release the target satellite 602 and apply a control medium to the target satellite 602, the control medium including a conductive material and / or a magnetic material. In particular, in this embodiment, the control medium includes a dispersed particulate matter 618 configured to be sprayed on the target satellite 602. Therefore, the satellite capture subsystem 614 may include a nozzle 616 as a control medium applicator. The nozzle 616 is configured to spray the particulate matter 618 on the target satellite. The nozzle 616 may be interconnected with a container (not shown) housed in the spacecraft 610 that contains the particulate matter 618. Particulate matter 618 may include nano-energetic composites, reactive metal compounds, or other conductive and / or magnetic materials, or combinations of materials suitable for being sprayed as particulate matter. Particulate matter 618 may be energized, for example, by an energy supply assembly 620 housed in spacecraft 610. In particular, particulate matter 618 releases energy to control target satellite 602.

[0026] In other examples, the controlled medium applicator may be configured to apply the auxiliary module and spray the particulate matter 618 onto the auxiliary module. For example, instead of or in addition to an auxiliary module including a layer of conductive and / or magnetic material, the particulate matter 618 may be sprayed onto the auxiliary module. In some examples, the controlled medium applicator may apply the auxiliary module onto the target satellite 602 and then use the nozzle 616 to spray the dispersed particulate matter 618 onto the auxiliary module.

[0027] In another example, the satellite capture subsystem 614 may include an ancillary module generator (not shown), as described above, configured to print or otherwise manufacture an ancillary module for attachment to the target satellite 602 and integrating the particulate matter 618. That is, the ancillary module may be manufactured by the ancillary module generator. The ancillary module generator may then apply (coat) the particulate matter 618 to the ancillary module and attach the ancillary module with the integrated particulate matter 618 to the target satellite 602.

[0028] In other implementations, the energy supply assembly may be remote from the target satellite and the control medium may be energized (powered) remotely. For example, referring to FIG. 7, an exemplary system 700 for controlling a target satellite 702 is depicted. The system 700 includes remote energy supply assemblies 710 and 720 for remotely energizing a control medium 704 coupled to the target satellite 702. The energy supply assembly 710 is disposed on Earth and includes a power transmission device 712. The power transmission device 712 may include a laser configured to emit a laser beam to remotely energize the control medium 704. In another example, the power transmission device 712 may include a microwave emitter configured to emit a microwave beam to remotely energize the control medium 704. In a further example, the power transmission device 712 may include a reflector configured to reflect sunlight toward the control medium 704 to remotely energize the control medium 704.

[0029] The energy delivery assembly 720 is disposed in space (e.g., on another satellite or spacecraft) away from the target satellite 702 and includes a respective power transmission device 722. The power transmission device 722 can include a laser configured to emit a laser beam to remotely energize the control medium 704. In another example, the power transmission device 722 can include a microwave emitter configured to emit a microwave beam to remotely energize the control medium 704. In a further example, the power transmission device 722 can include a reflector configured to reflect sunlight towards the control medium 704 to remotely energize the control medium 704.

[0030] 8, different control paths of a target satellite 802 with a control medium 804 are depicted. In one example, the control medium 804 may be energized to release energy to de-orbit the target satellite 802. In particular, the target satellite 802 follows a first path 810 to return the satellite to Earth, thereby de-orbiting the target satellite 802. In another example, the control medium 804 may be energized to release energy to move the target satellite 802 to a pre-designated region 822. In particular, the target satellite 802 follows a second path 820 to the pre-designated region 822. In a further example, the control medium 804 may be energized to release energy to propel the target satellite 802 to a new orbit 832 to extend the life of the target satellite 802. In particular, the target satellite 802 follows a third path 830 to the new orbit 832.

[0031] Referring now to FIG. 9, a flow chart of an exemplary method 900 for controlling a target satellite is depicted.

[0032] At block 905, the satellite control spacecraft captures the target satellite. In particular, the satellite control spacecraft may employ a propulsion system including an engine, one or more navigation components, and one or more means for detecting the target satellite to move the satellite control spacecraft in proximity to the target satellite. The satellite control spacecraft may further employ a satellite capture subsystem including one or more robotic arms, claws, magnetic components, tethers, meshes, etc., to capture the target satellite.

[0033] In block 910, the satellite control spacecraft applies a control medium to the target satellite. In particular, the control medium includes a conductive material and / or a magnetic material. For example, the conductive material and / or the magnetic material may include one or more of a reactive metal compound in a solid or liquid state, a reactive metal compound in a gas state, a polymer, a thermoplastic, a multi-coated metal with a metamaterial, and a nano-energetic material. The satellite control spacecraft may employ a satellite capture subsystem to apply the control medium to the target satellite.

[0034] For example, the control medium may be an auxiliary module attached to the target satellite. In some examples, the auxiliary module may be prefabricated and / or shaped to fit the target satellite. In some examples, the satellite capture subsystem may scan the target satellite and generate an auxiliary module that fits the shape of the target satellite based on the scan data. In some examples, the control medium may be a particulate matter configured to be sprayed on the target satellite. In yet other examples, the control medium may include a combination of the above, or other suitable control medium.

[0035] In block 915, the satellite control spacecraft releases the target satellite and the control medium coupled to the target satellite. More specifically, the satellite capture subsystem may release the target satellite.

[0036] At block 920, the energy supply assembly energizes the control medium to release energy to control the target satellite. In some examples, the energy supply assembly may energize the control medium to release energy to de-orbit the target satellite. In other examples, the energy supply assembly may energize the control medium to release energy to move the target satellite to a pre-designated region. In a further example, the energy supply assembly may energize the control medium to release energy to propel the target satellite to a new orbit to extend the life of the target satellite. In a further example, the energy supply assembly may energize the control medium to release energy to propel the target satellite to a new orbit to de-orbit the target satellite.

[0037] The energy delivery assembly may include an induction heating assembly configured to energize the control medium via induction heating. Thus, the energy delivery assembly may energize the control medium by orienting a coil of the induction heating assembly adjacent to the conductive and / or magnetic material of the control medium and passing a current through the coil to generate a magnetic field that inductively heats the control medium to energize the control medium. In some examples, certain components of the conductive and / or magnetic material may be selected to react and ignite at or below the Curie temperature of the material. Thus, the conductive and / or magnetic material may be energized to its reaction ignition point to combust the conductive and / or magnetic material. Thus, energizing the control medium may include energizing the conductive and / or magnetic material of the control medium to its reaction ignition point to combust the conductive and / or magnetic material.

[0038] In other examples, the energy supply assembly may remotely energize the controlled medium via a power transmission device. For example, remotely energizing the controlled medium may include emitting a laser beam to remotely energize the controlled medium. In other examples, remotely energizing the controlled medium may include emitting a microwave beam to remotely energize the controlled medium. In a further example, remotely energizing the controlled medium may include controlling a reflector to remotely energize the controlled medium. In other examples, remotely energizing the controlled medium may include other electromagnetic radiation (e.g., low frequency, infrared, ultraviolet, x-ray, gamma ray, terahertz, etc.) to remotely energize the controlled medium.

[0039] In a further example, the control medium can be pre-applied to the target satellite during the manufacturing process, i.e., the target satellite may be launched with the control medium such that after some predetermined period of time, a satellite control spacecraft can energize the control medium to control the target satellite.

[0040] Referring to FIG. 10, an exemplary method 1000 for controlling a target satellite is shown.

[0041] Optionally, at block 1005, the target satellite may be scanned and a model representative of the target satellite may be generated. In some examples, rather than scanning the entire target satellite, a region of interest (e.g., an area for deposition of a control medium) may be scanned. The region of interest may be utilized based, for example, on the size of the target satellite. The operations at block 1005 may be performed, for example, by a satellite control spacecraft as described above, for example, prior to launching the target satellite into orbit or while the target satellite is in orbit.

[0042] At block 1010, the control medium is applied to the target satellite. For example, the control medium may be sprayed. In another example, a model representing the target satellite or the region of interest may be used to generate an auxiliary module that includes the control medium that conforms to the shape of the target satellite or region of interest. The auxiliary module may then be applied to the target satellite in the region of interest (e.g., by gluing, fastening, or otherwise securing the auxiliary module).

[0043] Optionally, the target satellite may be launched into space and placed into orbit in block 1015. In particular, block 1015 may be performed when a control medium is applied to the target satellite prior to launch.

[0044] At block 1020, the controlled medium is energized. In some examples, it may first be determined whether a predetermined period of time has elapsed. For example, the auxiliary module may include a controller including a timing device to track the passage of time. If the predetermined period of time has elapsed, the auxiliary module may initiate inductive heating of the controlled medium to energize it and cause it to burn. In other examples, the passage of time may be tracked by an operator (e.g., a human operator or an automated tracking device external to the auxiliary module).

[0045] Such time tracking may allow a satellite to be placed in orbit for a predetermined period of time and then the control medium may be energized to change the orbit of the target satellite, for example the target satellite may be de-orbited and returned to Earth after the predetermined period of time or may be controlled to enter a different orbit for a further period of time.

[0046] In yet another example, multiple control media may be applied to a target satellite to be activated at different times to control the movement of the target satellite. Additionally, the conductive and / or magnetic materials of the control media may be selected to have specific ignition profiles to control the target satellite in a specific manner. In particular, certain components of the conductive and / or magnetic materials may be selected to have reaction ignition points at or below the Curie temperature such that the conductive and / or magnetic materials may be combusted to enable that specific control.

[0047] The scope of the claims should not be limited by the embodiments set forth in the above examples, but should be accorded the broadest interpretation consistent with the description as a whole.

Claims

1. 1. A system for controlling a target satellite, comprising: A spacecraft for controlling an artificial satellite, a propulsion subsystem configured to propel and navigate the spacecraft in proximity to the target satellite; and a satellite capture subsystem configured to capture the target satellite, apply a control medium to the target satellite, and release the target satellite, wherein the control medium includes particulate matter configured to be sprayed on the target satellite, and the control medium includes conductive and / or magnetic materials including reactive metal compounds including oxidizers and reducers; A spacecraft for controlling an artificial satellite, an energy supply assembly configured to energize the control medium to emit energy for controlling the target satellite; A system including:

2. The system of claim 1 , wherein the control medium includes an auxiliary module configured to attach to the target satellite.

3. 3. The system of claim 2, wherein said auxiliary module is shaped to conform to said target satellite.

4. The system of claim 2 , wherein the satellite capture subsystem further comprises a substrate printer configured to manufacture the auxiliary module.

5. The system of claim 2 , wherein the energy supply assembly is disposed within the auxiliary module.

6. The system of claim 1 , wherein the energy supply assembly is disposed on the spacecraft.

7. 2. The system of claim 1, wherein the energy supply assembly includes an induction heating assembly including a coil configured to be oriented adjacent to the conductive and / or magnetic material of the control medium, and a power supply circuit coupled to the coil to pass a current through the coil to generate a magnetic field for inductively heating the control medium to control the target satellite.

8. The system of claim 1 , wherein the energy supply assembly includes a power transmission device configured to remotely energize the control medium.

9. The system of claim 8 , wherein the power transmitter comprises one or more of a laser, a microwave emitter, an electromagnetic radiation emitter, and a reflector.

10. 10. The system of claim 1, wherein the conductive and / or magnetic materials further comprise one or more of a solid or liquid state reactive metal compound, a gas state reactive metal compound, a polymer, a thermoplastic, a multi-coated metal with a metamaterial, and a nano-energetic material.

11. 11. The system of claim 10, wherein certain components of the conductive and / or magnetic materials are selected to have a reaction ignition point below the Curie temperature of the material.

12. 12. The system of claim 11, wherein the energy supply assembly is configured to energize the conductive and / or magnetic materials of the controlled medium to the reaction ignition point to combust the conductive and / or magnetic materials.

13. 1. A method for controlling a target satellite, comprising: capturing the target satellite by a satellite control spacecraft; spraying a control medium onto the target satellite by the satellite control spacecraft, the control medium including dispersed particulate matter and the control medium including conductive and / or magnetic materials including reactive metal compounds including oxidizers and reducers; releasing the target satellite by the satellite control spacecraft; energizing the control medium by an energy supply assembly to release energy for controlling the target satellite; The method includes:

14. 14. The method of claim 13, wherein the step of energizing the control medium comprises energizing the control medium to release energy to de-orbit the target satellite.

15. 14. The method of claim 13, wherein the step of energizing the control medium includes energizing the control medium to emit energy to move the target satellite to a predesignated area.

16. 14. The method of claim 13, wherein the step of energizing the control medium includes energizing the control medium to release energy to propel the target satellite into a new orbit to extend the life of the target satellite.

17. The method of claim 13 , wherein the step of applying the control medium includes attaching an auxiliary module to the target satellite.

18. 20. The method of claim 17, further comprising prefabricating the auxiliary module to fit the target satellite prior to capturing the target satellite.

19. The step of energizing the control medium comprises: orienting a coil of the energy delivery assembly adjacent to the conductive and / or magnetic material of the control medium; passing a current through the coil to generate a magnetic field for inductively heating the control medium to energize the control medium for controlling the target satellite; 14. The method of claim 13, comprising:

20. The method of claim 13 , wherein the step of energizing the control medium comprises remotely energizing the control medium by a power transmission device.

21. 21. The method of claim 20, wherein remotely energizing the controlled medium comprises one or more of emitting a laser beam to remotely energize the controlled medium, emitting a microwave beam to remotely energize the controlled medium, emitting other electromagnetic radiation to remotely energize the controlled medium, and controlling a reflector to reflect sunlight to remotely energize the controlled medium.

22. 14. The method of claim 13, wherein the conductive and / or magnetic materials further comprise one or more of a reactive metal compound in a solid or liquid state, a reactive metal compound in a gas state, a polymer, a thermoplastic, a multi-coated metal with a metamaterial, and a nano-energetic material.

23. 23. The method of claim 22, wherein the particular components of the conductive and / or magnetic materials are selected to have a reaction ignition point below the Curie temperature of the material.

24. 24. The method of claim 23, wherein the step of energizing the controlled medium comprises energizing the conductive and / or magnetic materials of the controlled medium to the reaction ignition point to combust and / or sinter the conductive and / or magnetic materials.

25. 1. A method for controlling a target satellite, comprising: pre-applying a control medium to the target satellite by spraying, wherein the control medium includes dispersed particulate matter and wherein the control medium includes a reactive metal compound including an oxidizer and a reducer; launching the target satellite; energizing the control medium by an energy supply assembly to release energy for controlling the target satellite; The method includes:

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