Abstract: Systems and methods are operable maintain a proscribed Self Separation distance between an unmanned aircraft system (UAS) and an object. In an example system, consecutive intruder aircraft locations relative to corresponding locations of a self aircraft are determined, wherein the determining is based on current velocities of the intruder aircraft and the self aircraft, and wherein the determining is based on current flight paths of the intruder aircraft and the self aircraft. At least one evasive maneuver for the self aircraft is computed using a processing system based on the determined consecutive intruder aircraft locations relative to the corresponding locations of the self aircraft.

Abstract: The present disclosure relates to an unmanned aerial vehicle (UAV) able to harvest energy from updrafts and a method of enhancing operation of an unmanned aerial vehicle. The unmanned aerial vehicle with a gliding capability comprises a generator arranged to be driven by a rotor, and a battery, wherein the unmanned aerial vehicle can operate in an energy harvesting mode in which the motion of the unmanned aerial vehicle drives the rotor to rotate, the rotor drives the generator, and the generator charges the battery. In the energy harvesting mode regenerative braking of the generator reduces the forward speed of the unmanned aerial vehicle to generate electricity and prevent the unmanned aerial vehicle from flying above a predetermined altitude.

Abstract: An apparatus for controlling the formation flight of a trailing aircraft relative to a vortex generated by a leading aircraft includes a position module, peak-seeking module, limiter module, and control module. The position module is configured to determine a position of the vortex relative to the trailing aircraft. The peak-seeking module is configured to determine a desired position of the trailing aircraft for providing desired vortex-induced aerodynamic benefits based on the position of the vortex relative to the trailing aircraft and a mapping function of an individual performance metric. The limiter module is configured to modify the desired position of the trailing aircraft to avoid unintended crossings of the trailing aircraft into the vortex. Finally, the control module is configured to control flight of the trailing aircraft based on one of the desired position of the trailing aircraft and modified desired position of the trailing aircraft.

Abstract: The system (1) comprises means for determining the distance at the current time of the target aircraft (B) with respect to the merge waypoint (P0) along its path (TB), this distance being transmitted to calculation means in order to determine the speed control commands which are subsequently applied to the reference aircraft (A) in order for it to carry out the acquisition of the spacing at said merge waypoint (P0).

Abstract: An autonomous mobile device is configured to move on a surface provided with a base station thereon, and is operated in one of a work state and return state. In the work state, the autonomous mobile device is operable to plot a movement route along which the autonomous mobile device moves, and is operable to adjust the movement route upon presence of an obstacle. In the return state, the autonomous mobile device is operable to plot a returning route on the surface from the current position to the base station, and to move along the returning route to the base station.

Abstract: A technique to assist guidance techniques for a free-flying inspection vehicle for inspecting a host satellite. The method solves analytically in closed form for relative motion about a circular primary for solutions that are non-drifting, i.e., the orbital periods of the two vehicles are equal, computes the impulsive maneuvers in the primary radial and cross-track directions, and parameterizes these maneuvers and obtain solutions that satisfy constraints, for example collision avoidance or direction of coverage, or optimize quantities, such as time or fuel usage. Apocentral coordinates and a set of four relative orbital parameters are used. The method separates the change in relative velocity (maneuvers) into radial and crosstrack components and uses a waypoint technique to plan the maneuvers.