Momentum and reaction wheels for objects in space

Abstract

The spacecraft has a planar antenna array including an edge portion and a center portion. A reconfigurable reaction-momentum wheel is coupled to the antenna array for small roll and / or pitch of the antenna array. The reconfigurable reaction-momentum wheel has a reaction operating state or mode (high torque, low momentum) and a momentum operating state or mode (low torque, high momentum). A thruster is coupled to the antenna array for moving the antenna array.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application claims the benefit of priority to U.S. Application No. 63 / 161,677, filed March 16, 2021, the contents of which are incorporated herein by reference in their entirety. [Background technology]

[0002] This disclosure relates generally to wheels for use on objects in space, such as spacecraft. U.S. Patent Publication No. 2008 / 0099626 to William Bialke discloses a reconfigurable reaction wheel for a spacecraft, the entire contents of which are incorporated herein by reference.

[0003] U.S. Patent Nos. 9,973,266 and 10,979,133 show systems for assembling multiple small satellite antenna assemblies in space to form a large array. The entire contents of the '266 patent are incorporated herein by reference. As disclosed in the '266 patent, FIGS. 1(a) and 1(b) show a satellite communications system 10 having an array 30 of multiple common or small satellites 32 and a central or control satellite 20. The multiple small satellites 32 communicate with multiple end users 50 within a terrestrial footprint 40 and also with the control satellite 20, which in turn communicates with a base station gateway 60. Each of the small satellites 32 may include, for example, a processing unit (e.g., a processor or controller) and at least one antenna element. The control satellite 20 may also include a processing unit and at least one antenna or antenna element. Summary of the Invention

[0004] A spacecraft is provided having a planar antenna array including an edge portion and a middle portion. A reconfigurable reaction-momentum wheel is coupled to the antenna array and causes the antenna array to roll and / or pitch to a small extent (slightly, slightly). The reconfigurable reaction-momentum wheel has a reaction operating state or mode (high torque, low momentum) and a momentum operating state or mode (low torque, high momentum). A thruster is coupled to the antenna array and causes the antenna array to move. [Brief explanation of the drawings]

[0005] The accompanying drawings are incorporated into and constitute a part of this specification. It should be understood that the drawings illustrate only some embodiments of the present disclosure, and that other embodiments or combinations of various embodiments not specifically shown in the figures may still fall within the scope of the present disclosure. The embodiments will now be described in more detail with reference to the drawings.

[0006] [Figure 1(a)] Figure 1(a) shows a large array. [Figure 1(b)] Figure 1(b) shows a large array.

[0007] [Figure 2] FIG. 2 is a perspective view of a control satellite and a large array of multiple common satellites.

[0008] [Figure 3] Figure 3 shows a reconfigurable wheel with momentum and reaction modes.

[0009] [Figure 4(a)] Figure 4(a) shows the components of the satellite. [Figure 4(b)] Figure 4(b) shows the components of the satellite. [Figure 5] Figure 5 shows the components of a satellite.

[0010] [Figure 6] Figure 6 plots the torque and momentum accumulation for the chemical thruster, reaction wheel mode, and momentum wheel mode. Detailed Description

[0011] In describing the exemplary, non-limiting embodiments illustrated in the drawings, specific terminology will be relied upon for the sake of clarity. However, it is to be understood that the disclosure is not intended to be limited to the specific terminology so selected, and that each specific term includes all technical equivalents that operate in a similar manner to accomplish a similar purpose. While several embodiments have been described for purposes of illustration, it will be understood that the specification and claims are not limited to the illustrated embodiments, and that other embodiments not specifically shown in the drawings may be within the scope of the disclosure.

[0012] The system presented herein is an optimized system for maintaining the orientation alignment of a spacecraft with a large moment of inertia, combining traditionally separate functions into components for use. As described in U.S. Patent Publication No. 2008 / 0099626, a reconfigurable reaction-momentum wheel, when combined with other elements of an embodiment, is utilized in a system that provides one example of the present disclosure. However, other reconfigurable reaction-momentum wheels can be utilized within the spirit and scope of the present disclosure. As used herein, a reconfigurable reaction-momentum wheel is one or more disks or wheels housed in a single housing that can be selectively operated according to a reaction operating state or mode (high torque, low momentum) and a momentum operating state or mode (low torque, high momentum).

[0013] Turning to the drawings, Figure 2 shows a satellite communications system 100 for controlling a large, flat object in space. The system 100 includes a large phased array 300 and a control satellite 200 (Figure 5). As shown in Figure 2, the control satellite 200 may be coupled to an edge of one side of the phased array 300 and may be centrally located along that side. In other embodiments of the present disclosure, the control satellite 200 may be coupled to an inner portion of the phased array 300, such as the center of the phased array 300.

[0014] 2, 4(a), and 4(b), the array 300 includes a plurality (hundreds, possibly thousands) of discrete (independent) common satellites 302 coupled together by one or more connectors, coupling devices, or the like. The common satellites 302 are planar, i.e., the X and Y dimensions of the array 300 are significantly larger than the Z dimension, resulting in a large moment of inertia. In one embodiment, the common satellites 302 are antenna elements, and the array 300 is a phased antenna array.

[0015] Each common satellite 302 includes an antenna structure. In the exemplary embodiment shown in FIG. 4(b), the common satellite 302 may include numerous electronic components, including a common satellite processor 304, a front-end module (FEM) 310, a flight computer 306, one or more common satellite sensors 308, one or more common satellite flight actuators 314, solar collectors, and links to external systems. The solar collectors / solar cells generate energy from the sun. Excess power from the solar cells charges batteries, which may also power the electronic components. Each FEM 310 is associated with a respective antenna 312 for transmitting and receiving signals. Optionally, the common satellite 302 may also include thrusters.

[0016] The processing unit 304 controls the overall operation of the electronic components, including receiving / transmitting signals via the FEM 310. The flight computer 306 receives signals from sensors 308 regarding the orientation (heading, attitude) and position of the antenna structure 302. In response to signals received from these sensors, the flight computer 306 determines the current orientation and position and sends control signals to actuators 314 to position the antenna structure 302 appropriately. When multiple common satellites 302 are coupled together, they form a large array 300 in space.

[0017] 5, the control satellite 200 includes a processing unit 204, a flight computer 206, one or more control satellite sensors 208, one or more control satellite actuators 216, and one or more control satellite thrusters 218. The control processing unit 204 can control the operation of the control satellite 200, including the control satellite sensors 208, the control satellite actuators 216, and the gyro component 212. The control satellite sensors 208 can include, for example, a star tracker, a sun sensor, an inertial measurement unit, and a global position system unit.

[0018] A flight computer 206 on the control satellite 200 controls the position and orientation (azimuth, attitude) of the control satellite 200 and the phased array 300. The flight computer 206 receives sensor data from other sensors, such as a control satellite sensor 208 and a common satellite sensor 308, and determines the orientation (attitude) of the phased array 300. Based on the known and desired orientation of the phased array 300, the flight computer 206 commands multiple control satellite actuators 216 and common satellite actuators 314 on the common satellite 302, as needed, to ensure the phased array 300 is properly oriented. In one embodiment, the control satellite sensor 208 may be a GPS sensor that provides position data. In another embodiment, the control satellite sensor 208 may be an IMU (Inertial Measurement Unit), such as an accelerometer, that provides acceleration data from which position data can be determined.

[0019] As shown in FIG. 3 , the control actuator 216 may include a control actuator assembly 215. The actuator assembly 215 may include, for example, a support member 214 and one or more reconfigurable reaction-momentum wheels 216 a, 216 b, 216 c, and 216 d, and / or optional electromagnetic torque rods to prevent wheel saturation in low Earth orbit. In any orbit, disturbances ultimately affect the torque on the spacecraft. For example, a gravity gradient may cause the spacecraft to pitch down, which the reaction wheels counter-rotate to prevent. Because the gravity gradient excites a continuous torque, the wheel continues to rotate faster and faster until it reaches a maximum speed, or saturates. The torque rods themselves generate a force / torque that reduces the momentum (angular momentum) and thus the speed (speed of rotation) of the wheel. The torque rods are typically aligned in the X, Y, and Z coordinates and, in one embodiment, can be connected (directly or indirectly) to the wheel.

[0020] Wheel 216 may be any suitable wheel capable of controlling the position and / or orientation (heading, attitude) of control satellite 200, such as those described in U.S. Patent Publication No. 2008 / 0099626. Gyro component 212 may be, for example, an inertial measurement unit (IMU).

[0021] In an embodiment, the control satellite 200 has access to and authority to all sensor data from the multiple control satellite sensors 208 and / or common satellite sensors 308, and the multiple control satellite actuators 216 and / or common satellite actuators 314, and controls the overall orientation of the phased array 300 and the system 100. The control satellite flight computer 206 reads all sensor data from the multiple sensors 208, 308 and commands all actuators 216, 314. Each common satellite flight computer 206 on each small common satellite 302 reads only its own sensor data from its common satellite sensors 308 and controls its common satellite actuators 314 to correct its own orientation within the phased array 300.

[0022] Returning to Figure 2, the body housing 201 of the control satellite 200 is fixedly attached to the large phased array 300. The control satellite 200 may have a cube-shaped control satellite body 201. The control satellite body 201 houses (accommodates) the control satellite components shown in Figure 5, including the actuator assembly 215 (Figure 3).

[0023] Multiple common satellites 302 are interconnected to form a phased array 300 having a desired shape, shown here as a flat rectangle or square, although other suitable shapes, such as a circle, can be utilized. These common satellites 302 have flat, thin bodies 303, which allows the array 300 structure to be flat, thin, yet very large, heavy, and rigid or semi-rigid. While typical satellites each have the shape of a rectangular cube, the phased array 300 is a rectangular plate, whose mass extends significantly from the control point, the spacecraft 200, increasing the moment of inertia by a factor of two to three. These moments of inertia, when acted upon by the gravitational gradient of an orbiting planetary body, such as Earth, create a series of problems: A) For precise attitude control of system 100, an actuator that provides a larger torque than normal is required; B) An actuator that stores a larger momentum (momentum, angular momentum) than normal for system 100 is required; and C) An actuator that recovers large deviations from the nominal attitude (planned attitude) of system 100 is required.

[0024] The array 300 may have at least one edge portion (edge, fringe, end portion) formed by a peripheral satellite among the multiple common satellites 302. The control satellite 200 may be connected to one of the multiple common satellites 302 at one edge portion of the array 300. At the edge portion, the multiple thrusters 218 of the control satellite 200 can exert a larger angular torque, making it easier to control the pitch and yaw (pitch and roll, yaw angle) of the array structure 300. In other embodiments, the control satellite 200 may be connected at the center or middle portion of the array 300. At the edge portion, the moment of inertia is higher than in a center-mounted configuration, making the problem more severe.

[0025] In one exemplary embodiment of the present disclosure, the control satellite body 201 provides a housing for four chemical thrusters 218 ( FIG. 2 ). In one example embodiment, the housing 201 completely encloses the thrusters 218, as well as other components, including those shown in FIG. 5 . These thrusters 208 provide attitude control, including yaw (roll, about the Z axis), pitch (pitch, about the Y axis), and roll (roll, about the X axis). The four chemical thrusters 218 are arranged in a plus or cross pattern (aligned with the + / -Z and + / -Y axes) on the top, bottom, left, and right sides. The upper and lower chemical thrusters 218 generate thrust that is emitted upward and downward relative to the housing of the control satellite 200, thereby urging the edges of the phased array 300 downward and upward, respectively. Thus, the upper and lower thrusters 218 control the pitch (pitch) of the phased array structure 300. The left and right chemical thrusters 218 generate thrust that is discharged (fired) to the left and right, respectively, relative to the control satellite housing, thereby rotating the phased array structure 300 to the right and left, respectively. In this manner, the left and right thrusters 218 control the yaw (roll) of the phased array structure 300, causing it to rotate within its plane. Roll is controlled first by yawing using the "left and right" thrusters and then by using the "up and down" thrusters.

[0026] 2 and 3, the control satellite body 201 houses at least one actuator assembly 215 including one or more (at least one) reconfigurable reaction-momentum wheels (reaction / momentum wheels) 216. In the illustrated example embodiment, the body 201 completely encases (or at least partially encases) the reconfigurable reaction-momentum wheels 216. As shown, the wheels are flat, round, and extend in their respective planes. As used herein, the reaction-momentum wheels 216 in momentum mode rotate at a higher speed and can accumulate momentum, while the reaction-momentum wheels 216 in reaction mode rotate at a slower speed and can provide more torque. Thus, reaction mode allows for finer control and may be used, for example, to provide precise pointing (position control) and tilt (angle control) of array 300, while momentum mode can be used, for example, to provide coarse pointing (position control) of array 300 and coarse control for tilt or tilt recovery.

[0027] A large, flat, thin array 300 is desired to generate gyroscopic torques on the satellite and to counteract gravity gradients. In classical satellites with small deployable structures and low inertial momentum, the momentum (angular momentum) storage function is performed by wheels aligned with the primary rotational axes, yaw, pitch, and / or roll, depending on which axis is most affected by disturbance torques. Applying this principle to system 100, since gravity gradients act most strongly on the X and Y axes, wheels must be aligned with the roll and pitch axes for momentum management. Such a configuration requires a large number of wheels to achieve the required momentum storage capability. Alternatively, by placing multiple wheels on the yaw axis to generate gyroscopic torques and store momentum, the satellite can employ a pyramidal wheel arrangement, achieving the desired effect with fewer wheels. By generating a gyroscopic torque on the roll axis and utilizing the satellite's natural pitch axis rotation rate, the satellite maintains momentum around the zenith vector (Z). When a satellite points its momentum wheels toward the zenith, it will tilt left and right. Considering that a satellite can sometimes tilt left and sometimes tilt right, pointing the momentum vector normal to the array is the best option for pointing the satellite's momentum toward the zenith.

[0028] A plurality of wheels 216 are attached to a support member 214, which in turn is coupled to the control satellite housing 201. In the illustrated example embodiment, the support member 214 may have a pyramidal shape with triangular sides and a square base. The sides are perpendicular to one another. A wheel 216 is disposed on each of the four flat sides of the triangle. For example, the base of the support member 214 may be attached to the bottom of the housing 201, and fasteners (e.g., bolts) may be attached so as to extend through openings in the base of the support member 214. The wheels 216 may be exposed as shown, or may each be housed within a housing (not shown) that partially or completely encloses the wheels 216. The wheels 216 may be individually or simultaneously controlled to operate in a reaction or momentum mode of operation. Although all of the wheels 216 are shown mounted on a single, integrated support member 214, in other embodiments, there may be one separate support member 214 for each wheel 216, or multiple separate support members 214 may each have multiple wheels 216 mounted on them, which may be mounted at different locations within the control housing 201.

[0029] Thus, in the illustrated example embodiment, four reconfigurable reaction-momentum wheels 216 are provided, arranged in a four-wheel pyramid configuration. In the pyramidal configuration, the wheels 216 can be tilted toward the XY plane to increase reaction torque or momentum storage capacity in the XY plane while maintaining three-axis control of the entire satellite 100 with fault-tolerant redundancy, and tilting away can provide an inverted effect. In one example embodiment, the tilt can be 30-70 degrees based on the flight's moment of inertia. Using multiple reconfigurable reaction-momentum wheels arranged in a pyramidal configuration to control the satellite's gyroscopic torque and gravity gradient torque through momentum stored about the Z axis (which generates its own torque) is an important aspect of the present invention. Of course, fewer or more wheels 216 can be provided. Support 213 is attached, for example, to the bottom of 201 so that the coordinate systems are aligned. It may also include electronics for controlling the reaction-momentum wheel.

[0030] Thus, system 100 includes a dual-purpose wheel 216 combined with a chemical thruster 218, and in particular system 100 includes a satellite system. The system is oriented with a velocity vector in the +X direction. As shown, in certain embodiments, array 300 is planar, relatively flat, and can be large, thin, and heavy. The entire space system has a large mass and moment of inertia, making satellite array 300 difficult to control.

[0031] Attitude maneuvers utilize multiple reconfigurable reaction-momentum wheels 216 (Figure 3) and multiple chemical thrusters 218 (Figure 2). These wheels are set to specific orientations linked via an XYZ coordinate system. Positioning within the satellite is not critical; any suitable location can be utilized; the wheels do not need to be in the XYZ plane. As shown in Figure 6, the reaction wheel mode provides high torque capability for precise maneuvering. The momentum wheel mode provides higher momentum storage, allowing the spacecraft to counteract the momentum induced by the attitude rate required to track (orbit) the Earth. Wheels in momentum mode store more momentum at the expense of torque, but wheels in reaction mode can generate more torque than momentum wheels.

[0032] In one embodiment, system 100 combines a reaction mode of operation with a momentum mode of operation, allowing these wheels 216 to switch from high torque capability to momentum storage capability by dynamically changing the windings from parallel to series operation, which can be controlled by control processor 204 and / or common processor 304.

[0033] Four chemical propulsion thrusters aligned along the Y and Z axes (Figure 2) provide high-torque control of the pitch and yaw axes, enabling anomaly recovery and high-rate maneuvers not possible with torque induced by reaction wheels. The thrust generated by the Y-axis-aligned thrusters provides yaw control. The thrust generated by the Z-axis-aligned thrusters provides pitch control. The greater the moment arm (distance from the center of gravity), the greater the effectiveness of these thrusters. Reaction wheels are used to control yaw, pitch, and roll, but the torque they provide is a fraction of that provided by the reaction wheels. Furthermore, reaction wheels can saturate during high-torque, short-term maneuvers. The reaction wheels provide three-axis control during nominal operation, while the thrusters provide high-torque, high-rate control and maneuvers.

[0034] This embodiment optimizes for controlling large deployed structures in space, providing recovery in the event of large attitude disturbances or abnormal events, avoiding the need for excessively large reaction wheels, and combining reaction and momentum wheels to enable high-torque momentum cancellation based on the needs of the mission phase. Using chemical thrusters alone is undesirable due to the need to store large amounts of propellant in pressurized tanks, a problem exacerbated for multi-year missions. Using reaction wheels alone would result in oversized wheels to store the required momentum. Using momentum wheels alone would result in oversized wheels to provide the required torque. Using a combination of separate reaction wheels and separate momentum wheels would double the mass and volume, creating prohibitive packaging challenges and requiring existing reaction-momentum wheels. Example embodiments utilizing reconfigurable wheels to provide both reaction wheel and momentum wheel modes reduce space requirements.

[0035] It should be noted that there may be at least one (one or more) control satellites 200. Also, one or more control satellites 200 may not include a processing unit 204, flight computer 206, sensors 208, gyro components 212, solar collectors, batteries, or links. Rather, these wheels 216 may be mounted on a housing that is coupled to a structure or other object in space to control the object's orientation.

[0036] In the illustrated embodiment, the small satellite 302 and / or the central satellite 200 may include a processing unit for performing various functions and operations in accordance with the present disclosure. The processing unit may be, for example, a computing device, a processor, an application-specific integrated circuit (ASIC), or a controller. The processing unit may comprise one or more of a wide variety of components or subsystems, including, for example, a wired or wireless communication link and / or storage device(s), such as analog or digital memory or a database. All or a portion of the systems, processes, and / or data utilized in the present invention may be stored on or retrieved from the storage device. The processing unit may execute software, which may be stored on the storage device. Unless otherwise indicated, the processes are preferably performed automatically by the processor in substantially real time without delay.

[0037] In yet another embodiment of the present disclosure, data (such as position and attitude) can be transmitted from satellite 200 (e.g., by processor 204) to a ground station. The processor at the ground station can then determine necessary adjustments and / or other flight information and transmit control signals to satellite 200 (e.g., processor 204) to control the flight pattern (e.g., by use of actuators 216, 218, 212).

[0038] When structure 100 is configured as an antenna array, it (e.g., antennas 312 or antenna elements) communicates with, for example, user devices (e.g., user equipment such as cell phones, tablets, computers, etc.) and / or processing devices on Earth, such as a ground station. The present disclosure also includes methods for using structure 100 to communicate with (i.e., send and / or receive signals from) processing devices on Earth. The present disclosure also includes methods for processing devices on Earth to communicate with structure 100 (i.e., send and / or receive signals from) structure 100. Additionally, while structure 100 is used in low earth orbit (LEO) in the disclosed embodiment, it can be used in other orbits or for other applications. Furthermore, while the present system has been described for use with an array of antenna assemblies, it can be used in other applications, such as, for example, data centers, telescopes, reflectors, and other structures implemented either in space or on Earth.

[0039] Additionally, although multiple wheels 216 and thrusters 218 are shown as part of control satellite 200 with processor 200, these wheels 216 and / or thrusters 218 may be separate devices. For example, control satellite 200 may have its own housing, and the wheels and / or thrusters may have their own housing separate from the housing of the control satellite. Furthermore, these wheels and thrusters may be located inside the housing and / or outside the housing. The present application discloses a spacecraft having a planar antenna element, a reconfigurable reaction-momentum wheel coupled to the antenna element for slightly rolling and / or pitching the antenna element, and a thruster coupled to the antenna element for moving the antenna element. The planar antenna element may include an edge portion and may further include a housing coupled to the edge portion of the antenna element, the housing surrounding the reconfigurable reaction-momentum wheel. The thruster may be coupled to the housing. The thruster may provide a large thrust, and the reconfigurable reaction-momentum wheel may provide a small thrust. The spacecraft may have an antenna assembly including a plurality of planar antenna elements. The spacecraft may further include a plurality of planar antenna elements forming an antenna array with a midsection, and a housing coupled to the midsection of the antenna array, the housing surrounding the reconfigurable reaction-momentum wheel. Also disclosed is a communications system including a phased array in which multiple common antenna elements having a thin, planar structure are interconnected, the phased array including an outer portion; a controller including a housing coupled to the outer portion of the phased array; a plurality of reconfigurable reaction-momentum wheels housed within the housing for rolling and / or pitching the phased array structure; and a plurality of thrusters coupled to the housing for moving the phased array structure in multiple directions. The controller may include a satellite. The system further includes a control processor within the housing, which may operate the multiple reconfigurable reaction-momentum wheels and the multiple thrusters. The system may further include one or more sensors for detecting a position or orientation of the phased array structure. The control processor may operate the multiple reconfigurable reaction-momentum wheels and the multiple thrusters based on the detected position or orientation of the phased array structure. The controller may control a large structure deployed in space for both large attitude changes and precise attitude control. The reconfigurable reaction-momentum wheel may include a high-torque mode that provides high-precision attitude control. The reconfigurable reaction-momentum wheel may include a high-momentum mode that provides greater moderate attitude changes than the high-torque mode. The system may include a large attitude offset recovery capability using four chemical thrusters. The wheel may provide momentum cancellation at high torque based on the needs of the mission phase.

[0040] It will be apparent to those skilled in the art having the benefit of the teachings presented in the foregoing description and the associated drawings that modifications, combinations, subcombinations, and variations can be made without departing from the spirit or scope of the present disclosure. Similarly, the various embodiments described can be used individually or in combination with other embodiments. Those skilled in the art will appreciate that various combinations of embodiments not specifically described or shown herein will still fall within the scope of the present disclosure. In this regard, it should be understood that the present disclosure is not limited to the particular embodiments set forth, and that the embodiments of the present disclosure are intended to be illustrative, not limiting.

[0041] Additionally, where the method above or a method claim below does not expressly require an order in which its steps must be followed, or where no order is required based on the language of the description or claims, no particular order is intended to be inferred. Similarly, if a method claim below does not explicitly recite a step referred to in the description above, it should not be assumed that the step is required in the claim.

[0042] In addition, the drawings illustrate geometric terms or related terms such as flat, wheel, thin, top, bottom, right, left, side, rectangle, square, etc., and the description and claims may use geometric terms or related terms. These terms are not intended to limit the present disclosure, but are generally used for convenience to facilitate explanation based on the examples shown in the drawings. Furthermore, the geometric terms and related terms may not be precise.

Claims

1. 1. A spacecraft having an antenna array, further comprising: a plurality of reconfigurable reaction-momentum wheels coupled to the antenna array and capable of rolling or pitching the antenna array, each reconfigurable reaction-momentum wheel of the plurality of reconfigurable reaction-momentum wheels being disposed on a yaw axis of the spacecraft and tilted relative to at least two planes of a three-dimensional plane, and providing torque to a first plane corresponding to a roll axis of the spacecraft and a second plane corresponding to a pitch axis of the spacecraft; a thruster coupled to the antenna array and operable to move the antenna array; at least one processing unit configured to control the operating modes of the plurality of reconfigurable reaction-momentum wheels by dynamically varying the windings of the plurality of reconfigurable reaction-momentum wheels; the operational modes include a first operational mode in which the windings of the plurality of reconfigurable reaction-momentum wheels are operated in series to provide a first amount of torque and a first amount of momentum storage capability to the antenna array, and a second operational mode in which the windings of the plurality of reconfigurable reaction-momentum wheels are operated in parallel to provide a second amount of torque and a second amount of momentum storage capability to the antenna array.

2. In claim 1, the antenna array includes an edge portion, and a housing coupled to an edge of the antenna array, the housing enclosing the plurality of reconfigurable reaction momentum wheels;

3. In claim 2, The thruster is coupled to the housing.

4. In claim 1, the thruster is capable of providing a first magnitude of thrust, and each reconfigurable reaction-momentum wheel of the plurality of reconfigurable reaction-momentum wheels is capable of providing a second magnitude of thrust that is less than the first magnitude of thrust.

5. In claim 1, The antenna array comprises a planar antenna element included in an antenna assembly including a plurality of planar antenna elements.

6. In claim 1, a plurality of planar antenna elements forming the antenna array with an intermediate portion; a housing coupled to an intermediate portion of the antenna array, the housing enclosing the plurality of reconfigurable reaction-momentum wheels.

7. a phased array structure in which a plurality of common antenna elements having a thin planar structure are coupled to each other, the phased array structure including an outer portion; a controller including a housing coupled to the outer portion of the phased array structure; a plurality of reconfigurable reaction-momentum wheels housed within the housing and capable of rolling or pitching the phased array structure, each of the plurality of reconfigurable reaction-momentum wheels being tilted with respect to at least two planes of a three-dimensional plane with respect to a yaw axis of the phased array structure, and providing torque to a first plane corresponding to a roll axis of the phased array structure and a second plane corresponding to a pitch axis of the phased array structure; at least one thruster coupled to the housing and operable to move the phased array structure in a plurality of directions; at least one processing unit configured to control the operating modes of the plurality of reconfigurable reaction-momentum wheels by varying the windings of the plurality of reconfigurable reaction-momentum wheels; the operational modes include a first operational mode in which the windings of the plurality of reconfigurable reaction-momentum wheels are operated in series to provide a first amount of torque and a first amount of momentum storage capability to the phased array structure, and a second operational mode in which the windings of the plurality of reconfigurable reaction-momentum wheels are operated in parallel to provide a second amount of torque and a second amount of momentum storage capability to the phased array structure.

8. In claim 7, The system, wherein the control device includes a satellite.

9. In claim 7, further comprising a control processor within the housing; The control processor operates the plurality of reconfigurable reaction-momentum wheels and the at least one thruster.

10. In claim 7, The system further comprises at least one sensor capable of detecting a position or orientation of the phased array structure.

11. In claim 10, The controller operates the plurality of reconfigurable reaction-momentum wheels and the at least one thruster based on the detected position or orientation of the phased array structure.

12. In claim 7, The control system is capable of controlling a structure deployed in space for attitude changes and precise attitude control.

13. In claim 7, The system, wherein the first operating mode comprises a momentum operating mode.

14. In claim 13, The system, wherein the second mode of operation comprises a reaction mode of operation.

15. In claim 7, The system, wherein the at least one thruster provides an attitude offset recovery capability.

16. In claim 7, The system, wherein the plurality of reconfigurable reaction-momentum wheels are configured to provide momentum cancellation with torque based on the needs of a mission phase.

17. In claim 1, Each reaction-momentum wheel of the plurality of reconfigurable reaction-momentum wheels is tilted at an angle based on a moment of inertia of the spacecraft's flight path.

18. In claim 1, each reaction-momentum wheel of the plurality of reconfigurable reaction-momentum wheels is tilted at an angle between 30 degrees and 70 degrees relative to the at least two of the three-dimensional planes.

19. In claim 1, the plurality of reconfigurable reaction-momentum wheels includes at least four reconfigurable reaction-momentum wheels arranged to form a pyramid, each of the at least four reconfigurable reaction-momentum wheels forming a corresponding side of the pyramid.

20. In claim 1, The plurality of reconfigurable reaction-momentum wheels includes at least four reconfigurable reaction-momentum wheels arranged to form a pyramid.

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