Abstract: A landing station guidance-and-security system can include an environmental cover and/or a guide-and-security bar. In some embodiments, the landing station guidance-and-security system is integrated into a parcel-receiving device. In some embodiments, the landing station guidance-and-security system is configured to attach to a parcel-receiving device. In some embodiments, the guide-and-security bar includes a precision rod. In some embodiments, a drone landing station includes: a magnetic centering mechanism configured to center a drone and/or a package; sliding dovetail doors; a plow bar; at least one roll-up door; a first storage locker; a second storage locker; and/or a solid rear door configured to block access to the second storage locker from the first storage locker when the first storage locker is being accessed by a user.

Abstract: A container device and methods of operation and assembly of the same are provided. The container device is formed from a foldable material and includes interior locking mechanisms that prevent an inner box from being removed from an outer cover unless a user depresses a portion of the outer box to disengage an internal locking mechanism. A secondary locking mechanism prevents the inner box from being removed entirely from the outer cover.

Abstract: An operation of a spacecraft is controlled using an inner-loop control determining first control inputs for momentum exchange devices to control an orientation of the spacecraft and an outer-loop control determining second control inputs for thrusters of the spacecraft to concurrently control a pose of the spacecraft and a momentum stored by the momentum exchange devices of the spacecraft. The outer-loop control determines the second control inputs using a model of dynamics of the spacecraft including dynamics of the inner-loop control, such that the outer-loop control accounts for effects of actuation of the momentum exchange devices according to the first control inputs determined by the inner-loop control. The thrusters and the momentum exchange devices are controlled according to at least a portion of the first and the second control inputs.

Abstract: An operation of a spacecraft is controlled using an inner-loop control determining first control inputs for momentum exchange devices to control an orientation of the spacecraft and an outer-loop control determining second control inputs for thrusters of the spacecraft to concurrently control a pose of the spacecraft and a momentum stored by the momentum exchange devices of the spacecraft. The outer-loop control determines the second control inputs using a model of dynamics of the spacecraft including dynamics of the inner-loop control, such that the outer-loop control accounts for effects of actuation of the momentum exchange devices according to the first control inputs determined by the inner-loop control. The thrusters and the momentum exchange devices are controlled according to at least a portion of the first and the second control inputs.