The system is configured to generate a display of a tagging interface. The tagging interface may include a stitching selector. In response to a user selection of (1) a destination element that includes a first name identifier, (2) a source element that includes at least one of the plurality of pixels such that at least one of the plurality of pixels corresponding to longitude-time points comprising a second name identifier, and (3) the stitching selector, the system can be configured to indicate that the source element comprises the first name identifier.

A constellation of satellites and associated methods for Earth Observation are disclosed. One method includes transmitting a set of at least four signals towards the Earth using a constellation of at least four satellites and receiving a set of at least four reflected signals from the Earth using the constellation. The method also includes analyzing, using a set of at least four signal analyzers, the set of at least four signals to generate a set of data. Each satellite in the constellation individually houses a signal analyzer in the set of at least four signal analyzers. The method also includes deriving the set of Earth observations using the set of data. Each satellite receives a signal in the set of at least four signals from every other satellite in the constellation.

Disclosed herein are systems and methods for estimating an orbit of a satellite using only images captured by an onboard camera of the satellite. One of the disclosed methods includes: capturing a plurality of images using an onboard camera of the satellite; determining the trajectory, loop closure metrics, and the relative geographic position of the satellite using the plurality of images captured by the onboard camera; and estimating the orbit of the satellite based at least on the determined trajectory, loop closure metrics, and the relative geographic position of the satellite.

Disclosed herein are systems and methods for estimating an orbit of a satellite using only images captured by an onboard camera of the satellite. One of the disclosed methods includes: capturing a plurality of images using an onboard camera of the satellite; determining the trajectory, loop closure metrics, and the relative geographic position of the satellite using the plurality of images captured by the onboard camera; and estimating the orbit of the satellite based at least on the determined trajectory, loop closure metrics, and the relative geographic position of the satellite.

A method of roll steering of a spacecraft to align an aspect of the spacecraft, such as the surface of solar arrays carried by the spacecraft, to the sun, is described. The roll steering occurs only when the sun is at an angle (β) relative to the orbital plane of the spacecraft and when the spacecraft is not eclipsed by a body it is orbiting. This dayside-only roll steering of the spacecraft increases the power efficiency of the spacecraft. A spacecraft may include a controller which causes an attitude control subsystem to steer the spacecraft about a roll axis to position the surface of the solar array such that an axis normal to the surface of the solar array is aligned with the direction to a sun when the sun is visible to the spacecraft, and maintain a fixed orientation of the spacecraft about the roll axis when the sun is not visible to the spacecraft.

The disclosure relates to a method and apparatus of rotating mass attitude control. The method and apparatus entails rotating a mass to generate thrust. Varying the speed and direction of rotation provides some control of the magnitude and direction of the thrust generated. The method and apparatus of the invention pertinent to an attitude control system for spacecrafts or astromotive vehicles under conditions of zero to low gravity and atmosphere.

A glide control device includes a communications device configured to communicate with an attitude control device of a glide vehicle; and a processor configured to control the attitude control device. The processor is configured to control the attitude control device to generate a downward lift force when a velocity of the glide vehicle is higher than or equal to a first astronomical velocity.

When calculating a gimbal angle trajectory that satisfies boundary conditions set by an attitude boundary condition setter 2131 of the ground station 21, a gimbal angle trajectory calculator 2132 calculates the gimbal angle trajectory that minimizes a period of an acceleration interval within a range that satisfies driving restrictions of a gimbal, based on a gimbal angle θ.sub.0i of a start time and a gimbal angle θ.sub.ci of a fixed interval of an attitude change. Also, the gimbal angle trajectory is calculated that minimizes a period of a deceleration interval within a range that satisfies the driving restrictions of the gimbal, based on the gimbal angle θ.sub.ci of the fixed interval and a gimbal angle θ.sub.fi of a completion time of the attitude change. The obtained θ.sub.0i, θ.sub.ci, θ.sub.fi and an attitude change period τ are transmitted to the artificial satellite as gimbal angle trajectory parameters, and the control moment gyros are controlled based on the gimbal angle trajectory parameters.

When calculating a gimbal angle trajectory that satisfies boundary conditions set by an attitude boundary condition setter 2131 of the ground station 21, a gimbal angle trajectory calculator 2132 calculates the gimbal angle trajectory that minimizes a period of an acceleration interval within a range that satisfies driving restrictions of a gimbal, based on a gimbal angle θ.sub.0i of a start time and a gimbal angle θ.sub.ci of a fixed interval of an attitude change. Also, the gimbal angle trajectory is calculated that minimizes a period of a deceleration interval within a range that satisfies the driving restrictions of the gimbal, based on the gimbal angle θ.sub.ci of the fixed interval and a gimbal angle θ.sub.fi of a completion time of the attitude change. The obtained θ.sub.0i, θ.sub.ci, θ.sub.fi and an attitude change period τ are transmitted to the artificial satellite as gimbal angle trajectory parameters, and the control moment gyros are controlled based on the gimbal angle trajectory parameters.

An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.