Systems, computer-implemented methods and/or computer program products that facilitate measuring weight and balance and optimizing center of gravity are provided. In one embodiment, a system 100 utilizes a processor 106 that executes computer implemented components stored in a memory 104. A compression component 108 calculates compression of landing gear struts based on height above ground of an aircraft. A gravity component 110 determines center of gravity based on differential compression of the landing gear struts. An optimization component 112 automatically optimizes the center of gravity to a rear limit of a center of gravity margin.

Systems, computer-implemented methods and/or computer program products that facilitate measuring weight and balance and optimizing center of gravity are provided. In one embodiment, a system 100 utilizes a processor 106 that executes computer implemented components stored in a memory 104. A compression component 108 calculates compression of landing gear struts based on height above ground of an aircraft. A gravity component 110 determines center of gravity based on differential compression of the landing gear struts. An optimization component 112 automatically optimizes the center of gravity to a rear limit of a center of gravity margin.

Systems and methods for loading a cargo aircraft are described. The system includes at least one rail disposed in an interior cargo bay of a cargo aircraft that extends at an angle relative to an interior bottom contact surface of a forward portion of the interior cargo bay, through a kinked portion and an aft portion of the interior cargo bay. Payload-receiving fixtures are described that can be used in conjunction with the rail system, allowing for large cargo, such as wind turbine blades, to be transported by aircraft. Methods of loading a cargo aircraft can include advancing the large payload into the interior cargo bay of the aircraft such that at least one of the payload-receiving fixtures rises relative to a plane defined by the interior bottom contact surface of the forward portion of the interior cargo bay. Various systems, methods, components, and related tooling are also provided.

Systems, methods, and aircraft for managing center of gravity (CG) while transporting large cargo are described. Management of CG is achieved in many ways. In some instances, the aircraft itself is designed to assist in managing CG by providing fuel tanks that minimize the impact of fuel on the net CG of the aircraft. The fuel tanks utilize only a small amount of available volume in the wings for fuel. Disclosures related to properly managing CG while loading wind turbines onto cargo aircraft are also provided. The CG management techniques provided for herein allow for the transportation of wind turbine blades via aircraft, running counter to the typical rail or truck transportation of the same. One such management technique includes accounting for how a rotation of the blades when loading impacts the CG of the blades, and thus taking this into account when placing the blades in the aircraft.

An aerial drone system configured to serve as personal drone assistance is disclosed. The drone assistant is configured to follow the user and provide (1) audiovisual output including video, audio, and navigation, (2) environmental comfort including shade, light, misters for the benefit of the user, as well as (3) privacy and security. To provide audiovisual output, the drone is configured to track the user and maintain a constant height and distance relative to the user, preferably a few feet away in front of the user. To provide environmental comfort including shade, for example, the drone is configured to automatically maintain a position between the user and the sun, thus causing a shadow to be continually cast on the user. This shading is enhanced by specialized louvres and screens configured to prevent any direct sunlight from directly impinging on the user.

An aerial drone system configured to serve as personal drone assistance is disclosed. The drone assistant is configured to follow the user and provide (1) audiovisual output including video, audio, and navigation, (2) environmental comfort including shade, light, misters for the benefit of the user, as well as (3) privacy and security. To provide audiovisual output, the drone is configured to track the user and maintain a constant height and distance relative to the user, preferably a few feet away in front of the user. To provide environmental comfort including shade, for example, the drone is configured to automatically maintain a position between the user and the sun, thus causing a shadow to be continually cast on the user. This shading is enhanced by specialized louvres and screens configured to prevent any direct sunlight from directly impinging on the user.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

A solar unmanned aircraft is disclosed. The aircraft includes a first body, a second body, a main wing, a tail wing and at least four vertical control wings. The at least four control wings are all located below the main wing and the tail wing so that an upper surface of the main wing and tail wing can massively be installed with solar panels. Each of the vertical control wings has a fixed wing and a rudder. The rudder can rotate with respect to the fixed wing to control the attitude and motion of the solar unmanned aircraft.

A solar unmanned aircraft is disclosed. The aircraft includes a first body, a second body, a main wing, a tail wing and at least four vertical control wings. The at least four control wings are all located below the main wing and the tail wing so that an upper surface of the main wing and tail wing can massively be installed with solar panels. Each of the vertical control wings has a fixed wing and a rudder. The rudder can rotate with respect to the fixed wing to control the attitude and motion of the solar unmanned aircraft.