| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244164000 | Attitude control | 72 |
| 20080315039 | System and methods for space vehicle torque balancing - A spacecraft attitude controller balances external torques, including those resulting from gravity gradient and those resulting from other orbital disturbances, to achieve a comparatively stable, neutral attitude or orientation. Torque is balanced by selecting spacecraft attitude Euler angles and angular rates such that orbital disturbances and cross-coupling inertial effects are cancelled by the external forces, based on Euler's equation. A spacecraft attitude torque-balancing controller and related method compares spacecraft attitude angles and angular rates with an orbit reference frame, and provides instructions to conventional momentum management and propulsion controls to responsively adjust the spacecraft attitude and angular rates. This feedback loop drives to zero (or an acceptably small quantity) the rate of change of the difference between spacecraft and reference attitude and angular rates, thus minimizing the net accelerations on the vehicle. A further method is provided to determine a desired physical structure and mass distribution of the spacecraft, needed to achieve torque balancing in a spacecraft attitude such that appliances, such as antennas, solar panels, and instruments, will have the required orientation once in their final on-orbit deployed position. | 12-25-2008 |
| 20090057492 | SPACE VEHICLE HAVING A PAYLOAD-CENTRIC CONFIGURATION - In one aspect, a space vehicle includes a structure configured to expand from a first configuration to a second configuration and at least two equipment compartments attached to the periphery of the structure. The structure includes at least one of an antenna mesh, a light-shielding mesh, an optical reflector mesh and a net. | 03-05-2009 |
| 20100001142 | OPTIMIZED LAND MOBILE SATELLITE CONFIGURATION AND STEERING - A spacecraft may include a receive antenna, a transmit antenna having an antenna attitude adjuster, and a spacecraft attitude adjustor. The spacecraft may have a nominal orientation in which a yaw axis of the spacecraft, a roll axis of the spacecraft, and the radiator panels are substantially parallel to Earth's equatorial plane, in which the pitch axis of the spacecraft is substantially parallel to Earth's polar axis, in which the Nadir vector is in a yaw-pitch plane of the spacecraft, and in which the transmit antenna and receive antenna are oriented at angle φ | 01-07-2010 |
| 20100181430 | Steering Logic for Spacecraft Slew Maneuvers - Spacecraft control modules can steer a spacecraft during a slew maneuver. The spacecraft control modules can receive a target attitude for the spacecraft slew maneuver. An angle between a current attitude and the target attitude may be determined. A smooth attitude offset profile with respect to a steering frame may be established from the current attitude to the target attitude. A smooth attitude command may be generated from the smooth attitude offset profile. The smooth attitude command may be applied to an attitude control module of the spacecraft. | 07-22-2010 |
| 20130146714 | Method and System for Controlling a Set of At Least Two Satellites, Designed to Provide a Service on a Geostationary Orbit, Rendering Said Service on a Non-Geostationary Orbit - A method is provided for controlling a set of at least two satellites, designed to provide a service on a geostationary orbit, rendering said service on a non-geostationary orbit, in which means involved in the performance of said service, installed on board a satellite, are deactivated when the sun can damage it, and means involved in the performance of said service installed on board another satellite of the set are activated, when this is necessary to the continuity of the service. | 06-13-2013 |
| 20140166815 | TETHER FOR SPACECRAFT REACTION CONTROL SYSTEM - A spacecraft reaction control system comprising: a spacecraft having a center of mass; a length of tether extending from said spacecraft and offset from said spacecraft's center of mass and means for controllably changing said extension of said offset such that a variable force is exerted upon said spacecraft by said tether, said force being offset from said center of mass. | 06-19-2014 |
| 20140263844 | Component Deployment System - A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft. | 09-18-2014 |
| 20150060604 | Integrated Vehicle Fluids - A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks. The system is constructed in a modular configuration in which two redundant integrated fluid modules may be mounted to the vehicle, each of the modules capable of supporting the upper stage functions. | 03-05-2015 |
| 20160046394 | METHODS AND APPARATUS FOR PERFORMING PROPULSION OPERATIONS USING ELECTRIC PROPULSION SYSTEMS - Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control. | 02-18-2016 |
| 244165000 | By gyroscope or flywheel | 39 |
| 20080203230 | ATTITUDE CHANGE CONTROL METHOD, ATTITUDE CHANGE CONTROL SYSTEM, ATTITUDE CHANGE CONTROL PROGRAM AND PROGRAM RECORDING MEDIUM - Disclosed is an attitude change control system that is designed to efficiently output a torque for attitude change of a space craft using CMGs and realizes a real time CMG driving rule. A CMG gimbal steering law | 08-28-2008 |
| 20080223990 | SELF-POWERED SPACECRAFT ATTITUDE CONTROL SYSTEM AND METHOD - A system and method are provided for operating a control moment gyro (CMG) in a spacecraft. The CMG includes a spin motor, and a CMG rotor that is coupled to the spin motor and is configured to rotate about a spin axis. Electrical power from a power source is supplied to the spin motor to rotate the CMG rotor about the spin axis. A determination is made as to whether the power source can supply sufficient electrical power to the spin motor. If the power source cannot supply sufficient electrical power to the spin motor, the spin motor is rotated by the CMG rotor to generate and supply electrical power to the power source. | 09-18-2008 |
| 20080251646 | Singularity Escape and Avoidance Using A Virtual Array Rotation - Techniques for providing singularity escape and avoidance are disclosed. In one embodiment, a method for providing control moment gyroscope (CMG) attitude control singularity escape includes calculating a Jacobian A of a set of control equations, calculating a measure of closeness to a singularity, and comparing the calculated closeness to a threshold value, when the calculated closeness is less than or equal to the threshold value, recalculating the Jacobian A. Recalculating may include determining a new direction of virtual misalignment of β and γ, recalculating the Jacobian inputting the new direction of the virtual misalignment, recalculating the measure of closeness to a singularity, and comparing the measure of closeness to the threshold value. Further, the method may include calculating a gimbal rate command if the of closeness is greater than the threshold value and generating a torque from the gimbal rate command to control the attitude of a satellite. | 10-16-2008 |
| 20090039202 | Attitude Change Control Method, Attitude Change Control System, Attitude Change Control Program and Program Recording Medium - Disclosed is an attitude change control system that is designed to efficiently output a torque for attitude change of a space craft using CMGs and realizes a real time CMG driving rule. A CMG gimbal steering law | 02-12-2009 |
| 20090108136 | Navigation Body, Navigation Device, and Space Navigation Device - The present invention provides a thrust generator capable of generating thrust without using reaction of a combustion product, and a navigation body utilizing the same. The thrust generator has a rotation axis, a plurality of tops arranged symmetrically around the rotation axis, and a motor device for rotating the tops around the rotation axis. The spinning axis of the top is arranged along the radial direction of the rotation axis. The “top” generates a force by which it rises perpendicularly from the ground, that is, so-called couple of forces. By using the couple of forces, thrust is generated. | 04-30-2009 |
| 20090159753 | MOMENTUM MANAGEMENT SYSTEM FOR REACTION WHEEL BY USING NULL SPACE VECTOR AND METHOD - A reaction wheel momentum management method using a null space vector is provided. In accordance with this method, when any one of at least four reaction wheels used for triaxial control is made unavailable or degraded, a degraded wheel is used as long as possible for improving the mobility of the behavior of a satellite. The method provides momentum management for an N-number of reaction wheels W | 06-25-2009 |
| 20090200428 | CONTROL MOMENT GYROSCOPE - A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes an inner gimbal assembly (IGA), which, in turn, includes an IGA housing, a rotor rotatably coupled to the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the rotor about a spin axis. The CMG further comprises a stator assembly, which includes: (i) a stator assembly housing rotatably coupled to the IGA housing, and (ii) a torque module assembly coupled to the stator assembly housing and configured to rotate the IGA about a gimbal axis. A gimbal bearing is disposed between the IGA housing and the stator assembly housing. The gimbal bearing resides between the spin axis and the torque module assembly such that the distance between the gimbal bearing and the spin axis is less than the distance between the gimbal bearing and the torque module assembly. | 08-13-2009 |
| 20090218449 | ATTITUDE CONTROL DATA CREATING METHOD, AND ATTITUDE CONTROL SYSTEM APPLYING THE METHOD - In order to control an attitude of a movable object having a flexible member ( | 09-03-2009 |
| 20100006705 | Control Moment Gyro and Device for Assembly Thereof - Gyrodyne comprising an inertial wheel mounted, via a wheel support, on the moving part or rotor of a cardan assembly also comprising a stator and means of setting the rotor in rotation with respect to the stator about a first axis of rotation, it being possible for the spinner of said inertial wheel to be set in rotation about a second axis of rotation not aligned with said first axis of rotation, characterized in that said stator of said cardan is mounted on a block and fixed to said block via vibration-damping means, and in that said means of setting said rotor in rotation are at least partially housed in the interior volume of said block. | 01-14-2010 |
| 20100044517 | Control moment gyroscope array and method of power distribution therefor - An attitude control system for a spacecraft is disclosed that includes a scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a an output axis, wherein each gyroscope has a spin motor for spinning a rotor about a rotor axis and a gimbal torque motor for rotating the rotor about a gimbal axis, and wherein the system includes a generator for extracting kinetic energy from the rotors during rotor deceleration to power the gimbal torque motors of the gyroscopes. | 02-25-2010 |
| 20100059631 | UNIFIED ATTITUDE CONTROL FOR SPACECRAFT TRANSFER ORBIT OPERATIONS - A method of controlling attitude of a spacecraft during a transfer orbit operation is provided. The method includes providing a slow spin rate, determining the attitude of the spacecraft using a unified sensor set, and controlling the attitude of the spacecraft using a unified control law. The use of a unified set of sensors and a unified control law reduces spacecraft complexity, cost, and weight. | 03-11-2010 |
| 20100090065 | PRECISION ATTITUDE CONTROL SYSTEM FOR GIMBALED THRUSTER - A system for providing attitude control with respect to a spacecraft is provided. The system includes a reaction wheel control module configured to control a number of reaction wheel assemblies associated with the spacecraft in order to control attitude, and a maneuver control module configured to use a number of gimbaled Hall Current thrusters (HCTs) to control the total momentum associated with the spacecraft during an orbit transfer. The total momentum includes the momentum associated with the reaction wheel assemblies and the angular momentum of the spacecraft. Using the gimbaled HCTs to control the momentum associated with the reaction wheel assemblies during the orbit transfer results in minimal HCT gimbal stepping. | 04-15-2010 |
| 20100140413 | METHOD FOR MAXIMUM DATA COLLECTION WITH A CONTROL MOMENT GYROSCOPE CONTROLLED SATELLITE - The present invention relates to a method for maneuvering an imaging satellite, and more particularly a method for commanding control moment gyroscopes on an imaging satellite to change the attitude of the satellite. In one embodiment, a method for generating a gimbal rate trajectory for maneuvering a satellite to point to a target includes providing a final attitude for pointing to the target and a final satellite rate for imaging the target, providing an initial attitude and an initial set of gimbal angles, and determining a gimbal rate trajectory from the initial set of gimbal angles to a final set of gimbal angles. | 06-10-2010 |
| 20100193641 | Spacecraft Acquisition Maneuvers Using Position-Based Gyroless Control - A system and a method for commanding a spacecraft to perform a three-axis maneuver purely based on “position” (i.e., attitude) measurements. Using an “inertial gimbal concept”, a set of formulae are derived that can map a set of “inertial” motion to the spacecraft body frame based on position information so that the spacecraft can perform/follow according to the desired inertial position maneuvers commands. Also, the system and method disclosed herein employ an intrusion steering law to protect the spacecraft from acquisition failure when a long sensor intrusion occurs. | 08-05-2010 |
| 20100314499 | ACTUATOR WITH TRANSFER OF ANGULAR MOMENTUM FOR THE ATTITUDE CONTROL OF A SPACECRAFT - An attitude control actuator of a spacecraft includes a first momentum wheel driven in rotation by a motor and a second momentum wheel. Both momentum wheels are movable in rotation about an axis and are mechanically coupled by coupling means imposing between a rotation speed ω1 of the first momentum wheel and a rotation speed ω2 of the second momentum wheel a ratio R=ω2/ω1, negative on the one hand and continuously modifiable by the coupling means in response to a command on the other hand so as to modify the total angular momentum of the actuator while the total kinetic energy of the wheels are kept constant. In one embodiment, both momentum wheels have the same inertia and are coupled through a toroidal variator, where ratio R varies between −3 and −1/3. The motor drives the momentum wheels and operates as a generator for braking the momentum wheels. | 12-16-2010 |
| 20100320330 | CONTROL MOMENT GYROSCOPE BASED MOMENTUM CONTROL SYSTEMS IN SMALL SATELLITES - A self-contained momentum control system (MCS) for a spacecraft is provided for small satellites. The MCS features a miniaturized gyroscopic rotor with a rotational speed in excess of 20,000 RPM. The MCS includes at least three control moment gyroscopic mechanical assemblies (CMAs) rigidly mounted within a single enclosure, where each CMA mounted in an orientation whereby the longitudinal axis of each CMA is either orthogonal to every other CMA or is parallel to another CMA but in the opposite orientation. In order to further reduce the size of the MCS, an electronics package that is configured to interface command and control signals with and to provide power to the CMAs is included within the MCS enclosure. A plurality of shock isolation devices are used to secure each of the CMAs to the enclosure in order to reduce the launch load upon the CMAs thereby allowing the use of smaller rotor spin bearings. The MCS enclosure surrounding the CMAs and support structure is hermetically sealed. | 12-23-2010 |
| 20110006162 | ACTUATOR DEVICE FOR VARYING THE ATTITUDE OF A SPACECRAFT - An actuator device for varying the attitude of a spacecraft includes a reversible conversion chain of electrical energy to mechanical rotation energy of a flywheel. The electrical energy is stored in a capacitive element that may be a supercapacitor. The actuator device also includes an electrical power converter, connected, on one hand, to the capacitive element and intended to be connected, on the other hand, to the spacecraft power bus. The converter makes it possible to compensate for losses to keep a total energy of the actuator device constant. | 01-13-2011 |
| 20110011982 | MODULAR CONTROL MOMENT GYROSCOPE (CMG) SYSTEM FOR SPACECRAFT ATTITUDE CONTROL - A modular control moment gyroscope (CMG) system for a spacecraft attitude control system (ACS) is formed by a plurality of CMG modules, wherein each CMG module has a modular enclosure design that is identical to that of the other CMG modules, such that the plurality of CMG modules are mountable in a spacecraft array bus structure in any desired one of multiple array configurations. | 01-20-2011 |
| 20110101167 | METHODS AND SYSTEMS FOR IMPOSING A MOMENTUM BOUNDARY WHILE REORIENTING AN AGILE VEHICLE WITH CONTROL MOMENT GYROSCOPES - Methods and systems are provided for reorienting an agile vehicle, such as a satellite or spacecraft, using a control moment gyroscope (CMG) array. The CMG array comprises a plurality of CMGs onboard the agile vehicle. A method comprises obtaining an input torque command for reorienting the vehicle using the CMG array and, when the angular momentum of the CMG array violates or is approaching a momentum boundary criterion, decreasing the input torque command in the kinetic momentum direction, resulting in a modified torque command, and operating the CMG array using the modified torque command. | 05-05-2011 |
| 20110168848 | INNOVATIVE OPTIMAL SPACECRAFT SAFING METHODOLOGY - A system and method are disclosed for an innovative spacecraft (S/C) safing methodology. The system and method use wheel momentum to perform a rotisserie rotation so that the spacecraft can slew at a fast rate in a controlled fashion in order to keep the spacecraft power safe and maintain telemetry and command (T&C) coverage. The system and method involve a reaction wheel system and a spacecraft control processor (SCP). The SCP is in communication with the reaction wheel system. The SCP is operable to determine a rotisserie axis, and take the cross product of the rotisserie axis and a momentum vector to result in a unit vector. The SCP is further operable to slowly slew the spacecraft about the unit vector through an angle until the rotisserie axis aligns with the momentum vector, and rotate the spacecraft about the rotisserie axis to keep the spacecraft power safe. | 07-14-2011 |
| 20110186688 | Rotating space station torque eliminator - This invention uses existing technology to provide a means to initiate and control the rotation of a space station of the type proposed by Werhner von Braun in the 1950s, without the need for an external torque. This is accomplished by creating an angular momentum vector within the hub of the station which is precisely equal and opposite to that of the rest of the station. | 08-04-2011 |
| 20110248120 | PRECISION ATTITUDE CONTROL SYSTEM FOR GIMBALED THRUSTER - A system for providing attitude control with respect to a spacecraft is provided. The system includes a reaction wheel control module configured to control a number of reaction wheel assemblies associated with the spacecraft in order to control attitude, and a maneuver control module configured to use a number of gimbaled Hall Current thrusters (HCTs) to control the total momentum associated with the spacecraft. The total momentum includes the momentum associated with the reaction wheel assemblies and the angular momentum of the spacecraft. Using the gimbaled HCTs to control the momentum associated with the reaction wheel assemblies results in minimal HCT gimbal stepping. | 10-13-2011 |
| 20110297794 | METHOD OF NAVIGATING A SPINNING, ARTIFICIAL SATELLITE AND CONTROLLING THE GLOBAL, TERRESTRIAL SURVEILLANCE COVERAGE THEREOF - A method of controlling inertial attitude of an artificial satellite in order to perform a navigation function and to maximize terrestrial coverage of the Earth by the satellite. The method includes deploying the artificial satellite in an orbit about the poles of the Earth; applying gyroscopic precession to the artificial satellite spin axis to precess and maintain the satellite near the ecliptic pole; deploying the artificial satellite so that the spin axis is initially perpendicular to or substantially perpendicular to sun lines; and applying gyroscopic precession to the artificial satellite spin axis to precess the spin axis away from an initial deployed attitude at a selectively-variable precession rate and to maintain the spin axis perpendicular to or substantially perpendicular to a the sun lines. | 12-08-2011 |
| 20120160965 | METHOD TO ACHIEVE A RAPID AND LOW POWER SLEW OF A SATELLITE - A method includes providing two or more momentum wheels arranged for rotation on a spacecraft in a momentum-canceling set. The method further includes causing the two or more momentum wheels in the momentum-canceling set to rotate at momentum-canceling speeds. Additionally, the method includes reducing rotational speed of a momentum wheel in the momentum-canceling set to initiate a slew of the spacecraft. | 06-28-2012 |
| 20120199697 | ATTITUDE CONTROL SYSTEM FOR SMALL SATELLITES - Various embodiments of the present invention include an attitude control system for use with small satellites. According to various embodiments, the system allows rapid retargeting (e.g., high slew rates) and full three-axis attitude control of small satellites using a compact actuation system. In certain embodiments, the compact actuation system includes a plurality of single-gimbaled control moment gyroscopes (SGCMG) arranged in a pyramidal configuration that are disposed within a small satellite. | 08-09-2012 |
| 20120234981 | Split Flywheel Assembly With Attitude Jitter Minimization - Various embodiments of the present invention include assemblies and methods for minimizing the amplitude of attitude jitter. In one embodiment, a split flywheel assembly includes a plurality of independent concentric flywheels axially aligned and in operable engagement with one another such that each flywheel is configured to be independently controlled in order to manipulate the phase difference therebetween. | 09-20-2012 |
| 20120325970 | METHODS AND SYSTEMS FOR ADJUSTING ATTITUDE USING REACTION WHEELS - Methods and systems are provided for controlling attitude of a vehicle using a reaction wheel onboard the vehicle. One exemplary method involves receiving a torque command for adjusting the attitude of the vehicle using the reaction wheel, determining a phase error of the reaction wheel based at least in part on the torque command, and determining a motor torque command for the reaction wheel based on the phase error. The motor torque command is provided to an electric motor of the reaction wheel to apply a corresponding torque to the rotor of the reaction wheel. The relationship between the magnitude of the motor torque command and the magnitude of the phase error is nonlinear. In exemplary embodiments, the magnitude of the motor torque command exceeds the stiction torque, at least instantaneously, when the reaction wheel has fallen behind an expected position by more than a threshold amount. | 12-27-2012 |
| 20130082147 | Axial flux motor reaction wheel for spacecraft - The invention is for spacecraft reaction wheel with an axial flux dual Halbach rotor with an air coil stator. This wheel is more efficient and has fewer disturbances than a conventional reaction wheel with a brushless DC motor. | 04-04-2013 |
| 20130105633 | METHOD OF COMMANDING AN ATTITUDE CONTROL SYSTEM AND ATTITUDE CONTROL SYSTEM OF A SPACE VEHICLE | 05-02-2013 |
| 20130206915 | VERTICAL TAKE-OFF AND LANDING MULTIMODAL, MULTIENVIRONMENT, GYROPENDULAR CRAFT WITH COMPENSATORY PROPULSION AND FLUIDIC GRADIENT COLLIMATION - The invention relates to a vertical take-off and landing gyropendular craft or drone device (FIG. | 08-15-2013 |
| 20130221160 | SPACECRAFT ACQUISITION MANEUVERS USING POSITION-BASED GYROLESS CONTROL - A system and a method for commanding a spacecraft to perform a three-axis maneuver purely based on “position” (i.e., attitude) measurements. Using an “inertial gimbal concept”, a set of formulae are derived that can map a set of “inertial” motion to the spacecraft body frame based on position information so that the spacecraft can perform/follow according to the desired inertial position maneuvers commands. Also, the system and method disclosed herein employ an intrusion steering law to protect the spacecraft from acquisition failure when a long sensor intrusion occurs. | 08-29-2013 |
| 20140027577 | IMAGING SATELLITE SYSTEM AND METHOD - A system and method for deploying a satellite having an integrated bus and an aperture, wherein the integrated bus extends along its longitudinal axis and wherein the aperture intersects the longitudinal axis. The satellite is deployed into an orbit, wherein deploying includes orienting the satellite so that the aperture points at a desired location. The satellite is spun so that the logitudinal axis and the aperture remain pointing at the desired location and data regarding the desired location is captured via the aperture. | 01-30-2014 |
| 20140138491 | Spacecraft Momentum Unload and Station-keeping Techniques - Spacecraft momentum management techniques are coordinated with station-keeping maneuvers or other delta-V maneuvers. A body stabilized spacecraft attitude is controlled, the spacecraft including at least one momentum/reaction wheel, and a set of thrusters. A first momentum storage deadband limit is adjusted, the adjustment being related to a first delta-V maneuver window. A momentum management strategy is executed with the adjusted first momentum storage deadband limit such that a first thruster firing that performs desaturation of the momentum/reaction wheel also provides velocity change beneficial to the first delta-V maneuver. | 05-22-2014 |
| 20140209750 | Method and System for Unloading the Inertia Wheels of a Spacecraft - The method for unloading the inertia wheels of a spacecraft comprising three references axes X, Y, Z, the axis Z corresponding to a pointing direction, consists in inverting the direction of accumulation of the angular momentum in the wheels by automatic rotational flipping of the spacecraft about the axis Z, the pointing direction remaining fixed. The method has application to the field of satellites or of interplanetary probes. | 07-31-2014 |
| 20140209751 | REACTION SPHERE FOR STABILIZATION AND CONTROL IN THREE AXES - A system and method for controlling and stabilizing a satellite or other vehicle about any axis is disclosed. Embodiments achieve this three-axis control and stabilization with a spherical motor system or reaction sphere capable of storing momentum in a rotor. The spherical motor system comprises a spherical rotor having permanent magnets arranged in evenly-spaced antipodal pairs. Each of the permanent magnets are oriented with the same magnetic pole facing outward from a center of the rotor. The spherical motor system also comprises a stator which has magnetic sensors surrounding electromagnets. The spherical motor system further comprises a control system that controls timing and duration of energization of the electromagnets based on the detection of one of the permanent magnets by the magnetic sensors. Such a spherical motor system provides three-axis stabilization and control of a satellite (or other vehicle). | 07-31-2014 |
| 20140263845 | Space Vehicle and Guidance and Control System for Same - A space vehicle has a frame with a configuration of fiber optic gyroscopes (FOGs) and control moment gyroscopes (CMGs) at the outer perimeter of the frame. The FOGs and CMGs provide guidance and control for the space vehicle. This arrangement results in the largest possible FOG and CMG diameters, and therefore yielding the highest signal sensitivities and precision inertial control of vehicle orientation and pointing. Because the configuration places these guidance and control system components at the perimeter of the vehicle, it also provides a platform for multi-aperture signal channels in the interior of the vehicle by freeing up volume within the vehicle. | 09-18-2014 |
| 20150367968 | SYSTEMS AND METHODS FOR A MOMENTUM PLATFORM - Systems and methods for a momentum platform are provided. For example, a system for opposing torques includes a platform, wherein the platform is transportable to different locations in a zero-gravity environment and a plurality of momentum devices within the platform, wherein the plurality of momentum devices provide controllable angular momentum. The system also includes a torque feedback device, wherein the torque feedback device detects the torques experienced by the platform; a processing unit that controls the angular momentum of the plurality of momentum devices based on the torques detected by the torque feedback device such that the platform remains stable in response to the torques; and a mounting surface on the platform for attaching objects to the platform. | 12-24-2015 |
| 20160107769 | DEVICE, SYSTEM AND METHOD FOR ATTITUDE CONTROL - A control moment gyroscope (CMG) is provided, selectively having a first spatial configuration and a second spatial configuration at least during operation of the CMG. In the first spatial configuration the CMG occupies a smaller volume than in the second spatial configuration. For example, in the first spatial configuration no part of the CMG projects beyond a predetermined geometrical boundary, while in the second spatial configuration, a portion of the CMG projects beyond the geometrical boundary. | 04-21-2016 |
| 20160137318 | TRIPLE FLYWHEEL ASSEMBLY WITH ATTITUDE JITTER MINIMIZATION - Various embodiments of the present invention include assemblies and methods for minimizing the amplitude of attitude jitter. In one embodiment, a flywheel assembly for reducing the amplitude of attitude jitter is provided. The flywheel assembly includes a first flywheel, a second flywheel, and a third flywheel. The first flywheel, second flywheel, and third flywheel are axially aligned and in operable engagement with one another. Each flywheel is configured to be independently controlled in order to manipulate the phase difference therebetween. | 05-19-2016 |
| 244166000 | By magnetic effect | 1 |
| 20160004250 | Ultra High Speed Navigation Magnetic Satellite and Unmanned Aircraft - The present invention is about a new satellite or unmanned aircraft guided by earth's magnetic fields, instead of gravitational fields, as in the case of traditional satellites. This type of magnetic satellites can fly many times faster than traditional satellites, and sustain a much heavier load if necessary. In order to navigate in earth's magnetic fields, the magnetic satellite needs to be heavily charged. The charges, interacting with the magnetic field, induce a magnetic force, which replaces the gravitational force as the centripetal force for circular motion. | 01-07-2016 |
| 244168000 | By solar pressure | 3 |
| 20120138749 | Mobile solar power station and coupled solar power stations for space based power generation and transmission - A solar sail spacecraft is designed to steer and move in space by using solar radiation pressure as a driving force, therefore allowing fuelless propulsion, station keeping and attitude control. | 06-07-2012 |
| 20130292518 | DEVICE FOR MONITORING THE ATTITUDE OF A SATELLITE, AND METHOD FOR CONTROLLING A SATELLITE PROVIDED WITH SAID DEVICE - A device for controlling the attitude of a satellite exploiting solar pressure, includes at least two solar generators destined to be arranged on either side of a central body of the satellite and each having one face to be exposed to the Sun, referred to as “front face”, the device also including at least three surfaces whose optical properties can be commanded. The surfaces whose optical properties can be commanded are arranged on flaps connected to solar generators, each flap being fixed with respect to the solar generator to which it is connected, and such that, in the operating position, at least two of the surfaces are not parallel when the front faces of the solar generators are optimally oriented with respect to the Sun. The device further includes a module for commanding the optical properties of each surface whose optical properties can be commanded. | 11-07-2013 |
| 20160376032 | TORQUE GENERATION SYSTEM, ATTITUDE CONTROL SYSTEM FOR SPACECRAFT, AND RELATIVE POSITION AND VELOCITY CONTROL SYSTEM FOR SPACECRAFT - A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque. | 12-29-2016 |
| 244169000 | By jet motor | 15 |
| 20090020650 | SYSTEM AND METHODS FOR SIMULTANEOUS MOMENTUM DUMPING AND ORBIT CONTROL - The present system and methods enable simultaneous momentum dumping and orbit control of a spacecraft, such as a geostationary satellite. Control equations according to the present system and methods generate accurate station-keeping commands quickly and efficiently, reducing the number of maneuvers needed to maintain station and allowing station-keeping maneuvers to be performed with a single burn. Additional benefits include increased efficiency in propellant usage, and extension of the satellite's lifespan. The present system and methods also enable tighter orbit control, reduction in transients and number of station-keeping thrusters aboard the satellite. The present methods also eliminate the need for the thrusters to point through the center of mass of the satellite, which in turn reduces the need for dedicated station-keeping thrusters. The present methods also facilitate completely autonomous orbit control and control using Attitude Control Systems (ACS). | 01-22-2009 |
| 20090078829 | SYSTEM AND METHODS FOR SIMULTANEOUS MOMENTUM DUMPING AND ORBIT CONTROL - The present system and methods enable simultaneous momentum dumping and orbit control of a spacecraft, such as a geostationary satellite. Control equations according to the present system and methods generate accurate station-keeping commands quickly and efficiently, reducing the number of maneuvers needed to maintain station and allowing station-keeping maneuvers to be performed with a single burn. Additional benefits include increased efficiency in propellant usage, and extension of the satellite's lifespan. The present system and methods also enable tighter orbit control, reduction in transients and number of station-keeping thrusters aboard the satellite. The present methods also eliminate the need for the thrusters to point through the center of mass of the satellite, which in turn reduces the need for dedicated station-keeping thrusters. The present methods also facilitate completely autonomous orbit control and angular momentum control using. | 03-26-2009 |
| 20110121139 | STABILIZATION OF UNSTABLE SPACE DEBRIS - Disclosed herein, in certain embodiments, is a method of altering the stability of unstable space debris. In some embodiments, the method further comprises changing the orbit of the unstable space debris. | 05-26-2011 |
| 20110233343 | Satellite control system - In a satellite control system, a liquid is ejected by thermal ejection from holes in a substrate structure to create a reactive force on the satellite allowing the position, such as the attitude, of the satellite to be adjusted. | 09-29-2011 |
| 20110233344 | Satellite control system - In a satellite control system, a liquid is ejected by thermal ejection from holes in a substrate structure to create a reactive force on the satellite allowing the position, such as the attitude, of the satellite to be adjusted. | 09-29-2011 |
| 20120181387 | Inclination vector control with continuous or quasi-continuous maneuvers - A satellite inclination control method is provided. The method includes tracking optimal inclination vector control cycles for a satellite in near geosynchronous orbit, using control rates disposed to counter inclination growth of the satellite, where the control rates include continuously or quasi-continuously firings of a thruster, and where the control rates are disposed to provide convergence to the optimal inclination vector control cycles in the presence of variances in orbit determination, maneuver implementation and orbit propagation modeling errors. | 07-19-2012 |
| 20120187250 | Longitude-drift phase plane control with continuous or quasi-continuous maneuvers - A satellite longitude and drift control method is provided that includes providing a satellite that has a continuously or a quasi-continuously firing thruster, where the thruster is disposed to apply accelerations which counter a tri-axiality displacement in an orbit of the satellite, and the satellite thruster is disposed to achieve optimal ΔV performance in the presence of orbit determination and orbit propagation errors. The method further includes targeting an optimal two-phase continuous acceleration target cycle using the continuously or the quasi-continuously firing thruster, providing a closed loop and a hybrid loop implementation of the thruster firing, where the hybrid loop implementation includes an open and closed loop implementation, and where the closed loop and the hybrid loop implementations are disposed to provide quasi-continuous implementations of an optimal continuous control program. | 07-26-2012 |
| 20140145036 | ORBIT ATTITUDE CONTROL DEVICE, AND METHOD OF CONTROLLING ORBIT ATTITUDE - An orbit attitude control device includes a divert thruster including a plurality of nozzles. First group nozzles inject combustion gas in opposite directions along a first axis. Second group nozzles inject combustion gas in opposite directions along a second axis. A control section calculates correction values for opening degree commands based on a detection value of a pressure of the combustion chamber and a command value of the pressure, and corrects the opening degree command values by the correction values. The device further includes a first axis acceleration sensor for detecting acceleration along the first axis and a second axis acceleration sensor for detecting acceleration along the second axis. The correction values for the opening degrees of the first group nozzles are determined by a first axis acceleration, and the correction values for the opening degrees of the second group nozzles are determined by a second axis acceleration. | 05-29-2014 |
| 20140145037 | ORBIT ATTITUDE CONTROL DEVICE, AND METHOD OF CONTROLLING ORBIT ATTITUDE - An orbit attitude control device includes a plurality of nozzles for injecting combustion gas supplied from a combustion chamber, and a control section configured to calculate nozzle opening degree correction values so that a deviation between a detection value of the pressure of the combustion chamber and a command value becomes smaller. The control section is configured to calculate a total correction value so that the deviation between the detection value and the command values becomes smaller. A total value T1 for first group nozzles and a total value T2 for second group nozzles are calculated. The total correction value is distributed to the opening degree correction values for the first group nozzles with a ratio of T2/(T1+T2) and to the opening degree correction values for the second group nozzles with a ratio of T1/(T1+T2). | 05-29-2014 |
| 20140145038 | ORBIT ATTITUDE CONTROL DEVICE, AND METHOD OF CONTROLLING ORBIT ATTITUDE - An orbit attitude control device includes a plurality of nozzles and a control section. The nozzles inject a combustion gas supplied from a combustion chamber, opening degrees being controlled in accordance with opening degree command values. The control section calculates nozzle opening degree correction values for the opening degree command values in response to a detection value of a pressure of the combustion chamber and a command value for the pressure, and correct the opening degree command values by the nozzle opening degree correction values. Each nozzle opening degree correction value is determined based on each opening degree command value. | 05-29-2014 |
| 20140246543 | ATTITUDE CONTROL DEVICE FOR SPACE STATION WITH SYSTEM PARAMETER UNCERTAINTIES AND ON-ORBIT DYNAMIC DISTURBANCES - An attitude control device for space station with system parameter uncertainties and on-orbit dynamic disturbances. A plurality of state sensors measure a plurality of states of the space station. An identification frequency selecting device selects an identification frequency. A moment of inertia identification operator calculation unit calculates a moment of inertia identification operator. A moment of inertia identification device calculates moment of inertia of the space station. A disturbance torque identification device calculates disturbance torque. A control torque calculation unit calculates a control signal. A plurality of thrusters generate a control torque based on the control signal. | 09-04-2014 |
| 20150090841 | Transport Landing Vehicle - A transport landing vehicle for transferring an astronaut to and from an extraterrestrial mass such as a moon, asteroid, or small planet is disclosed. The transport landing vehicle has a cage that is substantially open to the outside environment. | 04-02-2015 |
| 20150307214 | THRUST NOZZLE SYSTEM AND METHOD FOR THE ORBIT AND ATTITUDE CONTROL OF A GEOSTATIONARY SATELLITE - A thrust nozzle system is provided for a satellite designed to be stabilized in autorotation over a geostationary orbit, the satellite comprising three reference axes X, Y and Z, the Y axis representing the North/South axis and the Z axis corresponding to an Earth pointing direction. The thrust nozzle system comprises a first set of thrust nozzles configured for maintaining the satellite in station, the first set comprising an even number of thrust nozzles using electrical propulsion, with a pre-adjusted orientation, the even number being equal to at least 4, the thrust nozzles being oriented along three spatial components, and having, taken in pairs, different signs of X and Y components. | 10-29-2015 |
| 20160376034 | SPACECRAFT AND ORBITAL PLANE CHANGE METHOD THEREFOR - A spacecraft | 12-29-2016 |
| 20190144140 | ARTIFICIAL SATELLITE AND THRUST BALANCE ADJUSTMENT METHOD | 05-16-2019 |
| 244170000 | By nutation damper | 1 |
| 20100019092 | SYSTEMS AND METHOD OF CONTROLLING A SPACECRAFT USING ATTITUDE SENSORS - A system for damping nutation and removing wobble of a spacecraft spinning about a given axis is provided. She system includes a sensor configured to determine three dimensional attitude measurements of the spacecraft, a processor operatively coupled to the sensor and configured to execute a process that facilitates aligning the spin axis with a spacecraft momentum vector. The processor, when executing the process, is programmed to receive spacecraft attitude data from the sensor, determine a torque command using the received attitude data, and control a momentum storage actuator on the spacecraft using the determined torque command such that an angular deviation about the given axis is reduced. | 01-28-2010 |
| 244171000 | With attitude sensor means | 4 |
| 20090001220 | Direct torque actuator control for control moment gyroscope - A control moment gyroscope system for delivering a target torque to a spacecraft including a rotor assembly having a rotor and a motor to spin the rotor about a rotor axis. A gimbal assembly has a gimbal for supporting the rotor assembly and a gimbal torque motor to rotate the gimbal about a gimbal axis, which is normal to the rotor axis, to generate an output torque. A control system has a sensor for determining the output torque and a processor in communication with the rotor assembly, the gimbal assembly and the sensor. The processor requests the target torque and establishes a feedback control loop to generate a torque error signal based on the output torque for bringing the output torque within a predetermined range of the target torque. | 01-01-2009 |
| 20110024571 | GYROLESS TRANSFER ORBIT SUN ACQUISITION USING ONLY WING CURRENT MEASUREMENT FEEDBACK - A system and method for gyroless transfer orbit sun acquisition using only wing current measurement feedback is disclosed. With this system and method, a spacecraft is able to maneuver itself to orient its solar panel to its maximum solar exposure spinning attitude. The disclosed system and method involve controlling a spacecraft maneuver using only the solar wing current feedback as the sole closed-loop feedback sensor for attitude control. A spin controller is used for controlling the spacecraft spin axis orientation and spin rate. The spin controller commands the spacecraft spin axis orientation to align with an inertial fixed-direction and to rotate at a specified spin rate by using a momentum vector. In addition, a method for estimating spacecraft body angular rate and spacecraft attitude is disclosed. This method uses a combination of solar array current and spacecraft momentum as the cost function with solar wing current feedback as the only closed-loop feedback sensor. | 02-03-2011 |
| 20110155858 | METHOD FOR CONTROLLING SATELLITE ATTITUDE, AND ATTITUDE-CONTROLLED SATELLITE - A method for controlling the attitude of a satellite in orbit around a celestial object, the satellite including an observation instrument, a solar panel, a radiator and a star sensor which are arranged on the satellite such that, in a reference frame associated with the satellite and defined by three orthogonal axes X, Y, and Z, the observation instrument has its observation axis parallel to the Z-axis, the solar panel is parallel to the Y-axis, the radiator is arranged on one of the sides −X, +Y, or −Y of the satellite, and the star sensor points to the negative X values side. The roll and pitch attitudes of the satellite are controlled during an activity period to direct the observation instrument towards areas of the celestial object to be observed, and the yaw attitude of the satellite is controlled to keep the sun on the positive X values side and ensure that a solar panel minimum insolation constraint is satisfied during observation phases of the activity period. | 06-30-2011 |
| 20140231589 | Gyroless Three-Axis Sun Acquisition Using Sun Sensor and Unscented Kalman Filter - An attitude estimator that uses sun sensor outputs as the only attitude determination measurements to provide three-axis attitude information. This is accomplished by incorporating the Euler equation into the estimator. An unscented Kalman filter is employed to accommodate various nonlinear characteristics and uncertainties of the spacecraft dynamics and thus improve the robustness and accuracy of the attitude estimate. | 08-21-2014 |
