A payload elevator system and method are disclosed, configured for providing a plurality of alternative payload elevator configurations, each payload elevator configuration being configured for transporting a payload module. A composite air vehicle configuration is also provided, including a respective payload elevator configuration, the payload elevator configuration being defined by and provided by the payload elevator system, and also including at least one payload module reversibly engaged to the payload elevator configuration via a corresponding engagement and release system.

This invention, the Motor-wing Gimbal Aircraft (MGA) is an aerial vehicle and waterborne craft. It launches and lands vertically from the ground and water. In flight, it transitions from vertical, hovering and forward flight to horizontal flight. The MGA embodies multiple configurations and arrangements of motor-wings, propulsion systems and hybrid engine combinations. The MGA uses a fly-by-light system for flight maneuvering and controlling the motorized multi-axis gimbal cockpit. The MGA uses cellular communications together with the Global Positioning System (GPS) for navigation, collision avoidance and restricted airspace avoidance. The MGA uses visible lights to signal its elevation and flight maneuvers. The MGA is constructed of modular apparatuses and assemblies that are interchangeable and work in concert to power and maneuver the vehicle. This invention includes: the method of construction, the method of control, the method of visual light signaling, the method of electronic mapping of airspace (EMA) and the method of navigation. This invention includes flight operation applications and military applications.

Disclosed herein are a vehicle system and method for VTOL. The vehicle system includes: a carrier vehicle and a cruise vehicle. The carrier vehicle includes one or more fuselages, one or more wings, one or more attach units coupled to the one or more fuselages or to the one or more wings, and propulsion systems operable to provide, at least, substantially vertical thrust and substantially horizontal thrust. The cruise vehicle includes one or more fuselages for carrying passengers or cargo and one or more wings. The one or more attach units of the carrier vehicle are adapted to couple to the cruise vehicle to detachably engage.

A takeoff and landing control method of a multimodal air-ground amphibious vehicle includes: receiving dynamic parameters of the multimodal air-ground amphibious vehicle; processing the dynamic parameters by a coupled dynamic model of the multimodal air-ground amphibious vehicle to obtain dynamic control parameters of the multimodal air-ground amphibious vehicle, wherein the coupled dynamic model of the multimodal air-ground amphibious vehicle comprises a motion equation of the multimodal air-ground amphibious vehicle in a touchdown state; and the motion equation of the multimodal air-ground amphibious vehicle in a touchdown state is determined by a two-degree-of-freedom suspension dynamic equation and a six-degree-of-freedom motion equation of the multimodal air-ground amphibious vehicle in the touchdown state; and controlling takeoff and landing of the multimodal air-ground amphibious vehicle according to the dynamic control parameters of the multimodal air-ground amphibious vehicle. The method is used for takeoff and landing control of a multimodal air-ground amphibious vehicle.

A cone shaped docking and releasing mechanism provides rigid connection between a parent UAV and a sub UAV to form a spliced double unmanned aerial vehicle system with improved cruising duration ability by providing sub UAV battery with charging function. It comprises a parent UAV, a sub UAV and a docking mechanism with charging ports. The parent UAV and the sub UAV are connected with each other through the docking mechanism to form a double UAV system, the docking mechanism is a cone structure and comprises a charging output component connected with the parent UAV internal control system, a charging circuit connected with a sub UAV control system and a charging input component connected with the charging circuit.

A method may be present for securing a strip in a structure. A first surface of the strip may be masked with a first tape. A surface of the structure may be masked with a second tape, the surface of the structure defining a desired shape. A sealant may be applied in a groove in the structure. The strip may be positioned in the surface such that a second surface of the strip contacts the sealant; and a caul plate may be pressed against the first surface of the strip, the caul plate including a set of ribs that contact the fairing strip, and the plurality of ribs defining a shape that substantially matches the shape of the surface of the structure. Pressing the caul plate against the first surface of the strip may cause sealant to pass between the set of ribs onto the tapes.

A system and method for participating in a multi-USV performance in three-dimensional space. The USV can include: a computer processor; a sensory device configured to detect live sensory information relative to a second USV participating in the performance in proximity to the USV; and a spatial control module executing on the computer processor and configured to enable the computer processor to: (i) receive instructions for performing a pre-determined sequence of spatial maneuvers of the performance; (ii) begin execution of the pre-determined sequence of spatial maneuvers according to the instructions; (iii) identify a modified sequence of spatial maneuvers calculated based on the live sensory information from the sensory device; (iv) halt execution of the pre-determined sequence of spatial maneuvers; and/or (v) execute the modified sequence of spatial maneuvers.

The disclosure provides a fixed wing UAV, with two propulsion propellers arranged parallel to each other and providing thrust for the UAV, or two traction propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two propulsion propellers or the two traction propellers respectively, wherein the thrust ratio provided by the two propulsion propellers or the thrust ratio provided by the two traction propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.

A system for air-launching a liquid fueled rocket launch vehicle using a tubular rocket support structure for holding the launch vehicle and for supplying the launch vehicle with make-up cryogenics, electrical power, and control signals, and for providing coupling to a launch-assist aircraft. The tubular rocket support structure contains cryogenic fluids, in addition to fuel and oxidizer, to cool the fuel and oxidizer during the pre-launch phase. The tubular rocket support structure has features that keep the liquid fuel and oxidizer from sloshing away from the tank outlet ports to the launch vehicle's rocket engine after release from the aircraft but before rocket launch. In operation, the aircraft controllably releases the tubular rocket support structure containing the launch vehicle, and the launch vehicle then launches from the rocket support structure.

Provided is a drone having a reconfigurable shape, more specifically, a drone having a reconfigurable shape that is capable of being horizontally flown without a rotation motion of the drone by configuring unit module drones having a rectangular parallelepiped shape that may apply thrusts in six directions and is capable of being flown singly or flown in various shapes by forming an assembly drone by coupling between the unit module drones.