The invention is methods for landing rockets with precision using deep reinforcement learning for control. Embodiments of the invention are comprised of three steps. First, sensors collect data about the rocket's physical landing environment, passing information to rocket's database and processors. Second, the processors manipulate the information with a deep reinforcement learning program to produce instructions. Third, the instructions command the rocket's control system for optimal performance during landing.

The invention is methods for landing rockets with precision using deep reinforcement learning for control. Embodiments of the invention are comprised of three steps. First, sensors collect data about the rocket's physical landing environment, passing information to rocket's database and processors. Second, the processors manipulate the information with a deep reinforcement learning program to produce instructions. Third, the instructions command the rocket's control system for optimal performance during landing.

A method for controlling a satellite using magnetics only, and a control system for implementing the method. The method involves assessing a current attitude of a satellite at a current time and location using magnetometry; setting a desired attitude for the satellite at a future time in a future location; developing a set of waypoints that provide the attitude of the satellite at plural locations between the current location and the future location; and actuating a plurality of magnetorquers to induce torques that achieve a small as possible difference between the attitude of the satellite between each waypoint and achieving the desired attitude at the future location, the magnetorquers being the sole means of inducing rotation of the satellite to attain the desired attitude.

A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises a plurality of capture arms attached to a grounding structure. In one embodiment, the capture arms are kinematically linked and are free to rotate with respect to the grounding structure using a single actuator, thereby synchronizing the rotation of the arms for any angular displacement of the actuator, thus the arms form a circle that is concentric with the boom axis. In a second embodiment, there are two sets of capture arms, with the arms in each set kinematically linked and independently actuated; thus, the two sets cooperatively form different grasping geometries. Further, the docking mechanism is configured to enable the host spacecraft to dock with the client spacecraft. The servicing spacecraft may also be configured to carry a robotic arm and a suite of end-effectors that can be automatically changed out on-orbit. The suite of end-effectors may include one configured with the disclosed capture mechanism, and another may be configured with the disclosed docking mechanism.

A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises a plurality of capture arms attached to a grounding structure. In one embodiment, the capture arms are kinematically linked and are free to rotate with respect to the grounding structure using a single actuator, thereby synchronizing the rotation of the arms for any angular displacement of the actuator, thus the arms form a circle that is concentric with the boom axis. In a second embodiment, there are two sets of capture arms, with the arms in each set kinematically linked and independently actuated; thus, the two sets cooperatively form different grasping geometries. Further, the docking mechanism is configured to enable the host spacecraft to dock with the client spacecraft. The servicing spacecraft may also be configured to carry a robotic arm and a suite of end-effectors that can be automatically changed out on-orbit. The suite of end-effectors may include one configured with the disclosed capture mechanism, and another may be configured with the disclosed docking mechanism.

The present disclosure describes autonomous flight safety systems (AFSSs) that incorporate an autonomous flight termination unit (AFTU) enabling AFSS monitoring for various termination conditions that are used to activate a flight termination system (e.g., in the event a termination condition is detected). Such termination conditions include boundary limit detection (e.g., whether a vehicle position is outside or projected outside a planned flight envelope), as well as body instability detection (e.g., whether a pitch rate and yaw rate exceed some threshold indicative of vehicle instability). For instance, an AFTU may incorporate a three-axis gyroscope sensor and may implement instability detection processing based on information obtained via the sensor. Instability detection processing may include, for example, a BID algorithm that may be implemented by an AFTU to monitor angular rates of the vehicle, to determine if the vehicle is no longer under stable control, and to issue termination commands when termination conditions are detected.

A method for attitude control of a satellite in inclined low orbit in survival mode is disclosed, the satellite including at least one solar generator, at least one solar sensor, magnetic torquers capable of forming internal magnetic moments in a satellite reference frame having three orthogonal axes X, Y, and Z, and inertial actuators capable of forming internal angular momentums in the satellite reference frame. The at least one solar sensor has a field of view at least 180° wide within the XZ plane around the Z axis, the method including a step of attitude control using a first control law, a step of searching for the sun by means of the at least one solar sensor, when a first phase of visibility of the sun is detected, and a step of attitude control using a second control law.

In a spacecraft for operating a thruster that includes a microwave source, a resonant cavity, and a source of propellant which the thruster converts to hot gas and directs via a nozzle to generate thrust, a method includes operating the thruster in an ignition mode in which the microwave source outputs power at a first rate, and operating the thruster in a propulsion mode in which the microwave source outputs power at a second rate higher than the first rate.

Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

A magnetically suspended control moment gyroscope comprising: a gimbal; a flywheel system, set in the gimbal; wherein the flywheel system comprises: a housing; a shaft, arranged in an inner cavity of the housing; a radial magnetic bearing, comprising: a first rotor portion and a first stator portion fixed to the shaft; an upper axial magnetic bearing and a lower axial magnetic bearing, wherein the upper axial magnetic bearing is fixed to an upper end of the first stator portion, the lower axial magnetic bearing is fixed to a lower end of the first stator portion; a wheel body, set in the radial magnetic bearing, fixed to the first rotor portion; an upper axial thrust plate and a lower axial thrust plate, wherein the upper axial thrust plate is fixed to an upper end of the wheel body, and is on an upper end of the upper axial magnetic bearing, the lower axial thrust plate is fixed to a lower end of the wheel body, and is under a lower end of the lower axial magnetic bearing.