Abstract: An example of the present disclosure provides a stereo camera assembly of an object tracking system. The stereo camera assembly comprises a wide-angle lens camera mounted on a mounting structure and a telephoto lens camera mounted on the mounting structure such that a field of view of the telephoto lens camera is at least partially encompassed by a field of view of the wide-angle lens camera.

Abstract: Presented are weight distribution systems for aircraft center of gravity (CG) management, methods for making/operating such systems, and aircraft equipped with CG management systems. A method is presented for managing the CG of an aircraft. The aircraft includes first and second landing gears and an airframe that removably attaches thereto one or more payloads and/or hardware modules. The method includes supporting the aircraft on a support leg that operatively attaches to the airframe and, while supported on the support leg, determining if the aircraft pivots onto the first or second landing gear. If the aircraft pivots onto either landing gear, the method responsively identifies a new airframe position for the payload/hardware module that will shift the aircraft's CG to within a calibrated “acceptable” CG range; doing so should balance the aircraft on the support leg. The payload/hardware module is then relocated to the new airframe position.

Abstract: An example of the present disclosure provides a stereo camera assembly of an object tracking system. The stereo camera assembly comprises a wide-angle lens camera mounted on a mounting structure and a telephoto lens camera mounted on the mounting structure such that a field of view of the telephoto lens camera is at least partially encompassed by a field of view of the wide-angle lens camera.

Abstract: Rotor assemblies for aircraft are described where one or more blades of the rotor assembly includes a blade alignment device that passively orients a blade in response to an airflow around the blade alignment device when the rotor assembly is free-wheeling. One embodiment comprises a method of operating a rotor assembly for aircraft. The method comprises operating the rotor assembly in a free-wheeling state, where the rotor assembly includes a rotary hub that rotates about an axis and a plurality of blades extending radially from the rotary hub. At least one of the plurality of blades includes a blade alignment device. The method further comprises aligning the at least one of the plurality of blades in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state.

Abstract: Rotor assemblies for aircraft are described that include a plurality of blades that are disposed vertically on a common axis along different horizontal planes. When the rotor assemblies are free-wheeling, the blades form a vertically stacked configuration, and when the rotor assembly is driven in rotation to generate lift, the blades bloom out from the vertically stacked configuration. At least one of the blades in the rotor assembly has a blade geometry that is different with respect to other blades such that when the blades are vertically stacked and free-wheeling, the collective shape of the blades is aerodynamic in shape, based on the different blade geometry, that reduces aerodynamic drag on the rotor assembly.

Abstract: Presented are weight distribution systems for aircraft center of gravity (CG) management, methods for making/operating such systems, and aircraft equipped with CG management systems. A method is presented for managing the CG of an aircraft. The aircraft includes first and second landing gears and an airframe that removably attaches thereto one or more payloads and/or hardware modules. The method includes supporting the aircraft on a support leg that operatively attaches to the airframe and, while supported on the support leg, determining if the aircraft pivots onto the first or second landing gear. If the aircraft pivots onto either landing gear, the method responsively identifies a new airframe position for the payload/hardware module that will shift the aircraft's CG to within a calibrated “acceptable” CG range; doing so should balance the aircraft on the support leg. The payload/hardware module is then relocated to the new airframe position.

Abstract: Methods and apparatus to project aircraft zone indications are disclosed. A disclosed example projection system for displaying an indicator pertaining to an aircraft includes a condition analyzer to determine a condition of at least one of the aircraft or a zone surrounding the aircraft, and a projector to project the indicator on or proximate the zone based on the determined condition.

Abstract: Methods and apparatus to project aircraft zone indications are disclosed. A disclosed example projection system for displaying an indicator pertaining to an aircraft includes a condition analyzer to determine a condition of at least one of the aircraft or a zone surrounding the aircraft, and a projector to project the indicator on or proximate the zone based on the determined condition.

Abstract: Rotor assemblies for aircraft are described that include a plurality of blades that are disposed vertically on a common axis along different horizontal planes. When the rotor assemblies are free-wheeling, the blades form a vertically stacked configuration, and when the rotor assembly is driven in rotation to generate lift, the blades bloom out from the vertically stacked configuration. At least one of the blades in the rotor assembly has a blade geometry that is different with respect to other blades such that when the blades are vertically stacked and free-wheeling, the collective shape of the blades is aerodynamic in shape, based on the different blade geometry, that reduces aerodynamic drag on the rotor assembly.

Abstract: Rotor assemblies for aircraft are described where one or more blades of the rotor assembly includes a blade alignment device that passively orients a blade in response to an airflow around the blade alignment device when the rotor assembly is free-wheeling. One embodiment comprises a method of operating a rotor assembly for aircraft. The method comprises operating the rotor assembly in a free-wheeling state, where the rotor assembly includes a rotary hub that rotates about an axis and a plurality of blades extending radially from the rotary hub. At least one of the plurality of blades includes a blade alignment device. The method further comprises aligning the at least one of the plurality of blades in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state.