The present invention relates to a novel rotator for a standardized coarse azimuth-pointing system for a balloon-borne platform—either zero pressure or Super Pressure Balloons (SPB)—with a maximum suspended payload of 5,500 lbs. The 5.5K Rotator novel shaft design, bearings, motor, and housing, result in a weight of the rotator being decreased by 33% from existing legacy rotators. The present invention achieved a 24% parts reduction from existing legacy rotators, and has the advantages of lighter weight, reusability, cost-effectiveness, machinability, and ease of assembly.

The present invention relates to a novel rotator for a standardized coarse azimuth-pointing system for a balloon-borne platform—either zero pressure or Super Pressure Balloons (SPB)—with a maximum suspended payload of 5,500 lbs. The 5.5K Rotator novel shaft design, bearings, motor, and housing, result in a weight of the rotator being decreased by 33% from existing legacy rotators. The present invention achieved a 24% parts reduction from existing legacy rotators, and has the advantages of lighter weight, reusability, cost-effectiveness, machinability, and ease of assembly.

A system for an unmanned aerial vehicle can include an altitude control system, which further includes a compressor assembly, a valve assembly, and an electronics assembly. The compressor assembly may include a driveshaft and a bearing assembly configured to rotate the driveshaft. The driveshaft may be formed from a first material and a compressor housing may be formed from a second material. The first and second materials may have different rates of thermal expansion. A dynamic preloading mechanism, such as a flexible plate, may be provided within the compressor assembly to exert a preloading force on the bearing assembly. Throughout the duration of the flight of the unmanned aerial vehicle, the preloading mechanism can continually compensate for differences in rates of thermal expansion between the first and second materials throughout.

A system for an unmanned aerial vehicle can include an altitude control system, which further includes a compressor assembly, a valve assembly, and an electronics assembly. The compressor assembly may include a driveshaft and a bearing assembly configured to rotate the driveshaft. The driveshaft may be formed from a first material and a compressor housing may be formed from a second material. The first and second materials may have different rates of thermal expansion. A dynamic preloading mechanism, such as a flexible plate, may be provided within the compressor assembly to exert a preloading force on the bearing assembly. Throughout the duration of the flight of the unmanned aerial vehicle, the preloading mechanism can continually compensate for differences in rates of thermal expansion between the first and second materials throughout.

An example arial image capture system captures a sequence of images from a camera attached to a flight vehicle while the flight vehicle moves in a lateral direction relative to underlying terrain and while concurrently rotating the camera along a circular path about an axis of rotation. The rotation of the camera controllably alters the camera's field-of-view to trace a curved swath of the underlying terrain with each rotation period of the camera around an area external to the camera's field-of-view.

An example arial image capture system captures a sequence of images from a camera attached to a flight vehicle while the flight vehicle moves in a lateral direction relative to underlying terrain and while concurrently rotating the camera along a circular path about an axis of rotation. The rotation of the camera controllably alters the camera's field-of-view to trace a curved swath of the underlying terrain with each rotation period of the camera around an area external to the camera's field-of-view.

A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and/or parafoil recovery.

A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and/or parafoil recovery.

A lighter than air platform an unfinned envelope having two or more propulsion elements coupled with the unfinned envelope proximate to the center of gravity. At least one navigation sensor is configured to monitor an actual flight path of the unfinned envelope, and at least one perturbation sensor is configured to monitor one or more perturbations of the unfinned envelope. A navigation controller is configured to guide the unfinned envelope with coordinated propulsion of the two or more propulsion elements. The navigation controller includes a navigation comparator that compares the actual flight path with a specified flight path of the unfinned envelope and determine a navigation instruction. A perturbation comparator compares the navigation instruction with the monitored one or more perturbations to determine a perturbation compensation. A propulsion coordinator controls propulsion values of each of the propulsion elements based on the navigation instruction and the perturbation compensation.

A balloon system including a balloon, a payload, and a safety module. A safety module, preferably including a tether and a parachute, and optionally including a cover and/or a drogue. A method of balloon system operation, preferably including operating the balloon system in flight and descending under a parachute.