Abstract: A controller system of an aerial vehicle may receive environmental data from one or more sensors of the aerial vehicle and adjusts limits of the aerial vehicle given the environmental conditions. When the aerial vehicle receives an input, such as a flight input from a remote controller or an environmental input such as a gust of wind, the controller system calculates appropriate motor inputs that are provided to the thrust motors of the aerial vehicle such that the adjusted limits of the aerial vehicle are not exceeded. In calculating the appropriate input to the thrust motors, the controller system performs an iterative process. For example, for a given maximum torque that can be applied to the thrust motors, the controller system iteratively allocates the torque such that torque components that are important for the stability of the aerial are first fulfilled, whereas subsequent torque components may be fulfilled or scaled back.

Abstract: A propulsion system includes at least one group of electric thrusters that are spatially distributed in a multi-axis system. A controller is in communication with each of the electric thrusters. The controller is configured to differentially throttle the thrusts of the electric thrusters with respect to propulsion force about two axes of the multi-axis system.

Abstract: Pulsating radio star (PULSAR) navigation systems and methods can include a plurality of PULSARs that can emit PULSAR radiation pulses in the millisecond range, and a plurality of Josephson Junctions (JJs) that can be arranged as an array of microantennas. The systems and methods can include a cryogenic cooling system for cooling the JJs to an operating temperature based on the JJ materials, and a thermal management system for maintaining the operating temperature. An oscillator can determine times of arrival (TOAs) of magnetic field components of the PULSAR pulses. A processor can compute the terrestrial position of the navigation system using the TOAs and the known celestial position of the PULSARs. A GPS sub-system can be included for navigation using GPS signals. The processor can be configured to compute terrestrial location using the PULSAR magnetic field components when GPS signal strength falls below a predetermined level or is lost.

Abstract: A satellite Automatic Identification System (AIS) for tracking maritime vessels includes a constellation of Low-Earth Orbit (LEO) satellites. Each LEO satellite includes an AIS payload for receiving AIS messages from the maritime vessels and determining therefrom reported vessel position data and satellite-based observation data. The system also includes an AIS reporting system configured to obtain the reported maritime vessel position data and satellite-based observation data from the LEO satellites over time. In addition, the AIS reporting system is configured to filter the reported maritime vessel position data and satellite-based observation data to recursively produce estimated maritime vessel positions and update the estimated maritime vessel positions for the maritime vessels.

Abstract: Embodiments of the present invention provide a positioning method. In those embodiments, the positioning method includes: receiving, by the first base station, an RTK measurement value for an RTK reference source; determining, by the first base station, first correction information according to the RTK measurement value, where the first correction information is correction information for positioning information obtained by the RTK reference source from a positioning system; sending, by the first base station, the first correction information to a first mobile terminal, so that the first mobile terminal determines a location of the first mobile terminal according to the first correction information.

Abstract: A flight vehicle attitude control system design device includes: a gain calculator calculating a proportional gain and a derivative gain from a system natural frequency and a system damping coefficient; a margin calculator calculating a gain margin and a phase margin from the proportional gain and the derivative gain; a grid generator generating a gain-phase margin grid from a relationship between the proportional gain and the derivative gain and a relationship between the gain margin and the phase margin; and a display unit outputting the gain-phase margin grid on a control gain design region having a gain margin as one of a horizontal coordinate axis and a vertical coordinate axis and a phase margin as the other one of the horizontal coordinate axis and the vertical coordinate axis.

Abstract: Multiple mode star tracker methods and systems in which attitude information and image information is generated are provided. The multiple mode star tracker includes a detector having a plurality of pixels arranged in a focal plane array. The detector is operated to obtain multiple image frames from within a field of view containing a plurality of stars. For each of the image frames, the attitude of the detector and in turn the attitude of each pixel is determined. Based on the attitude quaternion of the individual pixels within a plurality of frames, image data from the plurality of frames is co-added or stacked to form a composite image. The co-addition of multiple frames of image data enables or facilitates the detection of dim objects by the multiple mode star tracker.

Abstract: A dipole cancellation system and method may include a plurality of magnetometers for measuring a device magnetic field associated with a plurality of device coils generating a device magnetic field having a primary magnetic dipole moment. A compensating coil carrying a compensating current running a first direction that generates a compensating magnetic field having a compensating magnetic dipole moment. The compensating coil may be positioned and the first current may be selected so that the compensating magnetic dipole moment completely cancels the primary magnetic dipole moment. A method may use the system to stabilize a spacecraft by calculating an estimated torque of the spacecraft, receiving a value for an external magnetic field, receiving a value for a device magnetic field, and calculating and applying a compensating current may be then applied to the compensating coil to cancel the primary magnetic dipole moment, wherein the spacecraft is stabilized.

Abstract: A system for managing communication with a movable object includes one or more processors configured to receive a request for movable object data from a requester in a movable object environment, determine whether movable object data corresponding to the request is available in a cache associated with a movable object manager, and, in response to determining that the movable object data is available in the cache, provide the movable object data in the cache to the requester.

Abstract: A radiation hardened single board computer (SBC) includes a processor; synchronous dynamic random-access memory (SDRAM); non-volatile memory; a field programmable gate array (FPGA); and board-level physical layer interfaces.

Abstract: A control algorithm that determines one or more deviations in an orbit of a companion satellite, and control the companion satellite to minimize effects of perturbing forces.

Abstract: A method of testing a design of a satellite payload transponder with modules of radio frequency (RF) communications circuitry includes executing a modeling application for establishing a modeling environment for generating a virtual satellite payload transponder and virtual test equipment. The virtual satellite payload transponder has virtual modules of RF communications circuitry, with functionality equivalent to that of the satellite payload transponder with modules of RF communications circuitry. The virtual test equipment has functionality equivalent to that of physical test equipment in conjunction with modular test system software. The modeling environment establishes an executable block diagram for performing a simulation of executed satellite payload transponder command, RF signal performance and telemetry response testing, utilizing a given version of the modular test system software corresponding to the modules of RF communications circuitry of the design of the satellite payload transponder.

Abstract: Provided is a method of comparing satellite attitude control performances, the method including generating, by a controller, a satellite task execution command, receiving, by an input and output (I/O) unit, a result of a simulation performed on a satellite attitude control by a satellite attitude control simulator based on the satellite task execution command, and transmitting, by the I/O unit, the satellite task execution command to a satellite based on the result of the simulation.

Abstract: A system includes a computing device configured to implement a central user ground module that enables a user to emulate a plurality of central user ground nodes having fixed locations and that transmit and receive messages from at least one nanosatellite (nanosat), a second computing device configured to implement a remote user ground module that enables a user to emulate a plurality of remote user ground nodes that do not have fixed locations and that transmit and receive messages from at least one nanosat, and at least one additional computing device configured to implement a nanosat space module that emulates a nanosat, which transmits and receives messages from the ground nodes.

Abstract: According to one embodiment, an Optical Coherence Tomography (OCT) device includes: a light source; a mirror to reflect a light from the light source; a light receiver to output the light from the light source to skin and receive a light reflected from the skin; a detector to detect an interference signal between the light reflected from the mirror and the light received by the light receiver; an image sensor to convert the detected interference signal into an image signal; a processor to output a second signal by filtering a first signal based on the image signal, calculate an error by using the first signal and the second signal, and output an error-compensated image by compensating for the calculated error; and a display to display the error-compensated image. In this configuration, the OCT device may reduce noise caused by the image sensor, to display a skin image with improved quality.

Abstract: Provided is an apparatus for geometrically correcting an image from a geostationary remote sensing satellite, the apparatus being configured to perform the image navigation and registration on image data from a geostationary remote sensing satellite. The apparatus includes the landmark determination part configured to acquire landmark information associated with a first image and the navigation filter configured to calculate a state vector for correcting at least one of the attitude error, the orbit error, and the payload misalignment error with respect to the first image based on the landmark information.

Abstract: Disclosed herein are an automatic flight control system and method for an unmanned drone, in which a guidance system installed on a moving object transmits a guide signal, and the unmanned drone automatically flies based on the guide signal, thus allowing the unmanned drone to maintain a uniform distance from the moving object. The presented automatic flight control system for an unmanned drone is configured such that a guidance system transmits a guide signal based on a guidance request signal received from the unmanned drone, and the unmanned drone automatically flies depending on an automatic flight control value that is set based on an automatic flight guide signal when the guide signal is the automatic flight guide signal, and flies to the automatic control location set in response to an automatic location guide signal when the guide signal is the automatic location guide signal.

Abstract: A system may include a storage device that stores a set of instructions and a processor in communication with the storage device. When executing the set of instructions, the processor may be configured to cause the system to obtain, from a user terminal, a first geographical location via a network and obtain a second geographical location associated with a virtual parking region. The first geographical location may be determined by the user terminal according a GPS signal. The virtual parking region may include parking space for vehicles. The processor may also be configured to cause the system to determine whether a distance between the first geographical location and the second geographical location is less than a threshold and obtain information associated with the virtual parking region in response to the determination that the distance is less than the threshold.

Abstract: The use of an accelerometer for inertial navigation of a low thrust spacecraft undergoing acceleration wherein the inaccuracy of the accelerometer is less than the uncertainty in the accuracy of a modeled non-gravitational component of the acceleration that the spacecraft is undergoing is disclosed. A method of navigating a spacecraft having a low thrust propulsion system is also disclosed. The method comprises engaging the low thrust propulsion system, measuring the acceleration of the spacecraft using an accelerometer with an inaccuracy less than the uncertainty in the acceleration imparted by the low thrust propulsion system and acquiring a trajectory estimate using the measured acceleration. The trajectory estimate may be updated using an external reference navigation sensor.

Abstract: Systems and methods are provided for scheduling objects having pair-wise and cumulative constraints. The systems and methods presented can utilize a directed acyclic graph to increase or maximize a utilization function. Violation of cumulative constraints can be identified at the moment of constraint violation such that events resulting in constraint violations can be removed from the schedule while the schedule is being determined. By removing the events triggering constraint violations at the point of constraint violation, the systems and methods provided can determine optimal or near-optimal schedules in a relatively quick and efficient manner compared to systems and methods that check for violations of cumulative constraints after determining a schedule. The objects can comprise satellites in a constellation of satellites.

Abstract: Method and system for predicting collision probability of space objects are provided. Space objects are allocated according to a total number thereof for parallel computation in a GPU device. Initial orbit states of the space objects are generated by an initial-orbit-state generation kernel of the GPU device. Orbit propagation for each space object is performed based on the initial orbit state to predict a state of each space object by an orbit propagation kernel of the GPU device. The predicted states of the space objects are collected by a predicted-orbit-state collection kernel of the GPU device. A real-time visualization and rendering of the predicted space objects are performed in a form of point cloud during interactions between CPU threads and GPU kernels. A CPU host predicts a collision probability of any two space objects among the multitude of space objects, according to the interactions between the CPU threads and the GPU kernels.

Abstract: A layered architecture for customer payload systems is disclosed to provide a scalable, reconfigurable integration platform targeted at multiple unmanned aerial vehicles (UAV), and remove both UAV specific and payload equipment specific characteristics that increase complexity during integration. The layered architecture is a modular design architecture that is split by function. Standard interfaces are implemented between functional layers to increase reconfiguration possibilities and to allow reuse of existing components and layers without modification to the payload or UAV. The standard interfaces also promote easy connection and disconnection from other layer components. Additionally, once the layered architecture is implemented, technological or functional requirements changes can be isolated to one specific component layer, not the entire payload stack.

Abstract: Satellite transfer orbit search methods are described herein. One disclosed example method includes determining, based on boundary transfer orbits of a satellite, end points of an oblate epicycloid segment related to a transfer orbit of the satellite, and calculating, using a processor, a shape of the oblate epicycloid segment based on satellite data and the end points to define a search zone to determine a position of the satellite as the satellite moves along the transfer orbit.

Abstract: A method and apparatus are presented for providing a compact extended ephemeris package for GNSS processing. An extended ephemeris service provides orbit trajectories and clock corrections which are predicted into the future for navigation satellites. The extended ephemeris package format used allows the ephemeris information to be sent quickly and efficiently, even when using a low bandwidth communication network. Client GNSS receiver devices obtain the extended ephemeris package and extract the satellite ephemeris information for later use. This allows a client device to operate for many days or weeks without needing to decode or receive new satellite ephemeris information.

Abstract: A method and system for anti-interference compound on-line guidance in the atmosphere-entering stage of a Mars lander is provided in the present invention.

Abstract: A method is described for avoiding gyroscopic singularities during attitude correction to a system, such as a spacecraft having a CMG array. The method receives a corrective torque vector ? and gimbal angle values ? for each of at least three gimbals within the CMG array. The method generates a Jacobian matrix A as a function of gimbal angle values ?. The method calculates a determinant D of Jacobian matrix A. If the determinant is not equal to zero, it is not singular, and the method calculates a gimbal rate {dot over (?)} using a pseudo-inverse steering law equation. If the determinant is equal to zero, it is singular, and the method calculates a gimbal rate {dot over (?)} using a singularity avoidance steering law equation. The gimbal rate {dot over (?)} is output and can be applied to a CMG array resulting in applied torque to a spacecraft and attitude correction.

Abstract: Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for receiving data related to a first flight risk factor and a second flight risk factor where the first and second risk factors include one of: a proficiency risk factor, an equipment risk factor, an environmental risk factor, or a performance risk factor. Applying a first weighting to the first flight risk factor to generate a first weighted flight risk factor, and applying a second weighting to the second flight risk factor to generate a second weighted flight risk factor. Assessing a flight risk level for a flight based on the first weighted flight risk factor and the second weighted flight risk factor. Providing data indicating the assessed flight risk level for the flight for display to a user.

Abstract: A method and apparatus for reporting almanac versions and almanac identification by a mobile station to a server is provided. The server compares the almanac version and almanac identification held by the mobile station with almanac versions and almanac identifications held by the server. The server then sends instructions to the mobile station to match the server versions of the almanac versions and almanac identifications for the almanac versions and almanac identifications that the mobile station should hold.

Abstract: Device for receiving radio-navigation signals, for aiding the piloting of an aircraft, comprising a first master GNSS module and a second slave GNSS module which are dissimilar, the first master GNSS module comprising a first means for processing radio-navigation signals and a first means for computing guidance data (Xg), the second slave GNSS module comprising a second means for processing radio-navigation signals and a second means for computing guidance data (Xg) on the basis of the measurements provided by the said second means for processing signals, each GNSS module furthermore comprising a comparison means for comparing between the outputs Xg1,Xg2 of the said first and second means for computing guidance data, suitable for executing the following integrity test: |Xg1?Xg2|>Kg·?{square root over (Variance(Xg1?Xg2))} and for inferring an integrity defect if the said integrity test is satisfied.

Abstract: A propulsion system for the orbital control of a satellite with terrestrial orbit travelling with a speed of displacement along an axis V tangential to the orbit comprises two propulsion assemblies, fixed to the satellite facing one another with respect to the plane of the orbit, each of the propulsion assemblies comprising two propulsion modules; each of the propulsion modules successively comprising: a motorized link for rotation about an axis parallel to the axis V, an offset arm, and a platen supporting a propulsion unit able to deliver a thrust oriented along an axis perpendicular to the axis V; the two propulsion modules of each propulsion assembly being linked to the satellite on either side and substantially at equal distances from a plane perpendicular to the axis V passing through a centre of mass of the satellite.

Abstract: A control apparatus for an earth-distant-platform includes a control unit, which includes with a control input and a control output, and a memory element. The memory element contains a plurality of operating value parameter sets for an RF transmit amplifier unit. The control input receives a control signal and, dependent on the control signal, the control unit selects an operating value parameter set from the memory element. The control output controls an energy supply unit and/or a preamplifier/linearization element using the selected operating value parameter set such that the RF transmit amplifier unit is operable in a defined operating state.

Abstract: Methods and systems for determining a change of speed of an aircraft for enabling the avoidance of conflicts between aircraft trajectories. The method of determining a change in speed of an aircraft, comprises the steps of: defining a merge point and a tie point; monitoring a first aircraft; determining when the first aircraft passes the tie point; providing trajectory data; predicting a trajectory of a second aircraft using the trajectory data; defining a minimum permissible longitudinal spacing; predicting a longitudinal spacing between the first and second aircraft at the merge point based on the predicted trajectory; and if the minimum permissible longitudinal spacing is greater than the predicted longitudinal spacing then calculating a proposed change in speed of the second aircraft that will result in the longitudinal spacing between the first and second aircraft at the merge point being greater than or equal to the minimum permissible longitudinal spacing.

Abstract: The disclosure discloses a dynamic attitude measurement method of a star sensor based on gyro's precise angular correlation. On the basis that a dynamic compensation is performed on each of the measurement exposure frames of the star sensor and a fixed star matching vector matrix having dynamic error and noise influence is obtained in a prior art, a transform matrix between every two adjacent measurement frames of the star sensor is precisely measured by a unit including three gyros fixedly coupled with the star sensor. The transform matrix correlates the matched vector matrixes of the adjacent measurement frames of the star sensor. Finally, a correlated measurement equation is established with a series of correlated measurement frames, which is corresponding to processing a series of measurement frames as a single measurement frame.

Abstract: Methods and apparatuses are provided for managing a state of a platform. The methods and apparatuses comprise receiving a desired state for the platform. The methods and apparatuses comprise receiving the state of the platform. The methods and apparatuses comprise selecting a combination of thrusters from a plurality of thrusters to operate. The combination of thrusters is selected to adjust the state of the platform to the desired state. The methods and apparatuses operate the combination of thrusters to adjust the state of the platform to the desired state.

Abstract: A method and apparatus are presented for improving accuracy in a navigation system. A method of determining a physical characteristic of a receiving device in a navigation system, includes receiving a plurality of navigation signals from a plurality of navigation signal sources, respectively; determining a plurality of measurement estimates, based on the received navigation signals; and determining a physical characteristic of the receiving device by estimating a first set of one or more parameters in an error model, based on at least the plurality of measurement estimates. The error model includes a first error contribution for modeling noise and a second error contribution for modeling indirect signal propagation of the plurality of navigation signals.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for unmanned aerial vehicle authorization and geofence envelope determination. One of the methods includes maintaining, by a cloud system in wireless communication with Unmanned Aerial Vehicles (UAVs), allocated geofence envelopes for one or more of the UAVs, with each geofence envelope being a virtual barrier for a real-world geographic area. A request for approval of an updated geofence envelope is received from a first UAV in flight. The cloud system determines that the updated geofence envelope has not been allocated and/or the updated geofence envelope does not interfere with allocated geofence envelopes. In response to the determination, a response indicating approval of the request is generated. The generated response is provided to the first UAV.

Abstract: Methods and apparatuses are provided for managing a plurality of thrusters in a platform. The method and apparatuses comprise operating the plurality of thrusters in the platform with a thruster control system. The methods and apparatuses comprise estimating a vehicle response resulting from the operation of the plurality of thrusters to form an estimated vehicle response. The methods and apparatuses also comprise comparing the estimated vehicle response to a desired vehicle response to develop objective function errors. Also, the methods and apparatuses comprise developing a number of commands configured to correct the objective function errors.

Abstract: Three-axis spacecraft momentum management is performed for a spacecraft traveling along a trajectory, by an actuator including at least one thruster disposed on a single positioning mechanism. As the spacecraft travels along the trajectory, a desired line of thrust undergoes a substantial rotation in inertial space. When the spacecraft is located at a first location on the trajectory, the single positioning mechanism orients the thruster so as to produce a first torque to manage stored momentum in at least one of a first and a second of the three inertial spacecraft axes. When the spacecraft is located at a second location on the trajectory, the single positioning mechanism orients the thruster so as to produce a second torque to manage stored momentum in at least a third of the three inertial spacecraft axes.

Abstract: Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile.

Abstract: One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map.

Abstract: A computing device may detect that a space object has undergone a maneuver and may attempt to calculate a solution to that maneuver based in part on start and stop times and thrust uncertainties associated with the detected maneuver. However, the computing device may sometimes be unable to calculate an acceptable solution for a detected maneuver given these initial start and stop times and thrust uncertainties. Thus, the various embodiments provide for a computing device and methods implemented by a processor executing on the device for identifying and calculating a recovery maneuver of a space object when an acceptable solution for a detected maneuver cannot be determined. In the various embodiments, a computing device processor may generate a recovery maneuver based on the detected maneuver, and the processor may adjust the start and stop times and the uncertainty values of the recovery maneuver until an acceptable solution is found.

Abstract: Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.

Abstract: Systems and methods for performing airport surface collision-avoidance. A wingtip-mounted camera allows the pilot to positively ascertain that the wingtip will clear objects located in the video. An exemplary system implemented on an aircraft includes a wingtip module having a camera that generates a video stream and a communication device that transmits the generated video stream. A processor receives the video stream and generates a reticule for the video stream. A display device simultaneously presents the video stream and the reticule. The reticule includes a horizon line and is based on a focal length of a lens of the camera and height of the camera above ground. The reticule includes curved and/or straight distance lines and curved or straight travel lines. The travel line(s) correspond to at least one aircraft component or a zone of importance and are based on location of the camera and trajectory of the aircraft.

Abstract: A methodology for initial orbit determination of an object about an astronomical body searches a grid of possible boundary values on the range-to-object over the observation interval to find the grid point and corresponding initial orbit that best fits all of the three or more (N) angles-only observations according to an error metric. The search is conducted by solving a boundary-value problem (e.g. Lambert's Problem) for different grid points. The state vector is propagated to determine estimated observation directions for the remaining N?2 observations. The grid point (and initial orbit) that best fit all of the observations is selected. The grid may be searched by testing each and every point on the grid or by using other optimization techniques such as hill climbing algorithms to find the optimal grid point. For efficiency, the search may start with a broad but coarse initial grid and increase the resolution of the grid as the search converges to a solution.

Abstract: An ephemeris refinement system includes satellites with imaging devices in earth orbit to make observations of space-based objects (“target objects”) and a ground-based controller that controls the scheduling of the satellites to make the observations of the target objects and refines orbital models of the target objects. The ground-based controller determines when the target objects of interest will be near enough to a satellite for that satellite to collect an image of the target object based on an initial orbital model for the target objects. The ground-based controller directs the schedules to be uploaded to the satellites, and the satellites make observations as scheduled and download the observations to the ground-based controller. The ground-based controller then refines the initial orbital models of the target objects based on the locations of the target objects that are derived from the observations.

Abstract: In a system and method for navigating a moving object according to signals from satellite, a moving object receives satellite navigation signals from a number of satellites. The moving object also receives moving base data from a moving base. The received moving base data includes satellite measurement data of the moving base. At the moving object a relative position vector of the moving object relative to the moving base is determined, based on the received moving base data and the received satellite navigation signals. The moving object sends a signal reporting information corresponding to the relative position vector.

Abstract: In one or more embodiments, an apparatus and method for operating an unmanned and autonomous vehicle includes a sensor management module configured to direct sensors as to what function they are to provide; a mission management module configured to provide execute function capabilities; an effects management module configured to provide launching and directing weapons to their target capabilities; a vehicle management module; a situation awareness management module configured to provide correlate sensor data of objects, threats, targets, geographic points of interest that the pilot requires in the immediate environment; a communications management module; an information management module configured to provide a database of intelligence-related data; a middleware module configured to interface with the sensor management module, the mission management module, the effects management module, the vehicle management module, the situation awareness management module, the communications management module, and the inf

Abstract: Technologies are generally described for controlling a flight path of a UAV based image capture system for solid modeling. Upon determining an initial movement path based on an estimate of a structure to be modeled, images of the structure to be modeled may be captured and surface hypotheses formed for unobserved surfaces based on the captured images. A normal vector and a viewing cone may be computed for each hypothesized surface. A set of desired locations may be determined based on the viewing cones for the entire structure to be modeled and a least impact path for the UAV determined based on the desired locations and desired flight parameters.

Abstract: A system includes a fluid reservoir containing a first fluid, a pair of fluidic channels in fluidic connection with the fluid reservoir, a counter-fluid reservoir having a second fluid that is non-miscible with the first fluid, and a pump connected to the fluid reservoir. The pump is configured to pump the first fluid from the fluid reservoir into the pair of fluidic channels. When contained in a vehicle, the system allows for control of the vehicle's orientation. The system may use sensor input to determine when to actuate the pump. Each fluidic channel may have a cross-section that varies along its length. The fluidic channels may be geometrically symmetric about the fluid reservoir. The system may be incorporated into a vehicle to control the vehicle's orientation.

Abstract: A method for operating a controlled device. A feedback signal is received from a controlled device, the feedback signal indicating actual system dynamics of the controlled device. A predefined limit is applied to the actual system dynamics to create limited system dynamics. A modulation parameter is calculated by a processor based at least in part on the limited system dynamics and the actual system dynamics. Desired system dynamics for the controlled device are generated by the processor based at least in part on the modulation parameter and an external command.