A vehicle capable of computing an optimal attitude path that provides increased solar power generation through snap-roll events during orbital transfer maneuvers. A vehicle may include a memory and processor, including instructions that, when executed, can generate an attitude profile of the vehicle during an orbital transfer; identify, from the attitude profile, a snap-roll event, the snap-roll event is a violation event in which movement of the vehicle violates a body-frame angular rate constraint, wherein the snap-roll event is identified based on the first vector and the second vector being in substantial alignment; identify a plurality of control points along a trajectory of the vehicle during the snap-roll event; and adjust angular velocity of the vehicle at a first control point in the plurality of control points, wherein a first angular velocity of the vehicle at the first control point exceeds a maximum angular velocity of the vehicle.

A system for estimating stability margins of a vehicle includes one or more sensors configured to collect telemetry data during execution of an operational maneuver by a vehicle, wherein the operational maneuver is performed as part of a planned operational sequence of one or more maneuvers, one or more processors, and memory storing instructions that, when executed by the one or more processors, cause the system to process the telemetry data to determine a transfer function of a control system of the vehicle, the processing including applying one or more transformations to the telemetry data based on an order of a reference input command associated with the operational maneuver, and estimate one or more stability margins of the vehicle control system based on the transfer function.

A nanosatellite configured for launching from a cube satellite launcher is disclosed. The nanosatellite has a lower portion sized to the fit within the launcher housing, and has top, bottom, left, right, front and rear sides forming a payload housing. The top side has a top surface configured to engage with a front end of the spring of the launcher. The nanosatellite has an upper portion extending from the top surface of the lower portion, and is sized to fit within the spring of the launcher. A control subsystem contained within the upper portion. The nanosatellite may have one or more a solar panel arrays connected to the lower portion. In some embodiments, the solar arrays are movable between a stowed position against the lower portion and a deployed position extending outwardly from the lower portion. An additional 1U-3U of payload may be connected to the lower portion.

The present disclosure provides a system for autonomously docking a spacecraft, the system comprising: one or more electromagnets; one or more sensors; and a controller. The controller configured to: identify a target; cause movement of the spacecraft closer to the target; determine a change in an orientation of the one or more electromagnets and the mating adapter on the target; and adjust a current in the one or more electromagnets to produce a torque, wherein the torque causes the spacecraft to align with the target.

Independently moving deployment and positioning space vehicles that are configured to deploy and/or position structures are disclosed. The deployment and positioning vehicles work together to deploy and/or maintain the position/shape of a space structure. The deployment and positioning vehicles may include one or more thrusters, an attitude determination and control system (ADCS), a precision vehicle-to-vehicle location determination system, processing circuitry, etc. Two or more deployment and positioning vehicles are configured to coordinate the deployment and/or positioning of the space structure themselves or in concert with the other deployment and positioning vehicles in the deployment and positioning vehicle network, as well as achieve precision positioning.