Abstract: A system includes a satellite structure and a dedicated Payload Attaching Fitting PAF for releasable attachment to said satellite structure. The satellite structure an external load-carrying structure; and external vertical planar panels. The external vertical planar panels have internal reinforcements or embedded structures or skin thickness reinforcements, each configured for exerting the structural reinforcement function of diagonal beams in a truss structure architecture.

Abstract: Systems, methods, and apparatuses for the direct mount of secondary payload adapters to a truss structure common to a space vehicle payload adapter are disclosed herein. In one or more embodiments, a method for reacting loads into a space vehicle payload adapter comprises reacting, by more than two interstitial rings of the space vehicle payload adapter, the loads created by secondary payloads mounted onto the space vehicle payload adapter, into a truss structure of the space vehicle payload adapter. The method further comprises reacting, by struts of the truss structure, the loads to a forward ring and an aft ring of the space vehicle payload adapter. In one or more embodiments, the reacting of the loads maintains high frequency (e.g., greater than (>) thirty (30) gigahertz (GHz)) modes for the space vehicle payload adapter.

Abstract: A landing zone arrangement is disclosed for aircraft capable of vertical take-off. The arrangement includes a plurality of segments that form a landing zone in an operating state, a storage space for at least partially storing the segments in a stored state, and a base with a rotatable rotor element in order to rotate the segments for transfer between the operating state and the stored state. The landing zone arrangement allows a lighter technical design as the individual segments are removably secured to the rotor element, and a securing unit of the arrangement is designed to fasten the removable segments to the rotor element for transfer into the operating state and to release this fastening for transfer into the stored state. A lifting unit is provided in order to move the removable segments in the direction of the rotor element when transferring into the operating state.

Abstract: An exemplary ducted fan includes a duct having a central longitudinal axis, a rotor hub and stator hub extending along the central longitudinal axis, rotor blades extending from the rotor hub, each of the rotor blades operable to rotate about its own pitch-change axis, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length, stators extending from the stator hub to an interior surface of the duct, each of the stators having a stator leading edge and a stator thickness, and a first separation between the rotor plane and the stator leading edge of not less than approximately 1.5 times the stator thickness.

Abstract: A combined vertical takeoff and landing UAV having a large vertical takeoff and landing UAV, a connecting device, and a small vertical takeoff and landing UAV. The connecting device having a clamping component and an adsorption component. The clamping component includes a clamping part, and a clamping groove is arranged on the clamping part. The clamping component having a snap-fitting part, and a snap-fitting groove is arranged on the snap-fitting part. The clamping groove and the snap-fitting groove are correspondingly set. A first holding space is arranged on the clamping part, and a second holding space is arranged on the snap-fitting part. The adsorption component comprises a first magnetic element located in the first holding space, and the adsorption component also comprises a second magnetic element, which is located in the second holding space.

Abstract: An unmanned aerial vehicle (UAV) for transporting a payload is provided. The UAV comprises a body and one or more propellers rotatably connected to the body. The UAV further comprises a battery mounted to the body. The battery is releasable from the bottom of the UAV. The UAV further comprises a payload container mounted to the body. The payload container is releasable from the bottom of the UAV to a landing platform associated with a UAV station.

Abstract: An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, a line having one end coupled to the chassis and an opposite free end, wherein the free end is positioned below the chassis, and a severing mechanism operable to sever the line under control of the control system.

Abstract: A heat dissipation structure includes a housing configured to accommodate a heating element of an unmanned aerial vehicle (UAV). The housing includes a first air vent and a second air vent. The first air vent is configured to guide an airflow into the housing. The airflow includes a propeller-generated airflow generated by a propeller of the UAV during rotation. A side projection of the first air vent on a side of the housing at least partially overlaps a side projection of the propeller on the side of the housing. The second air vent is configured to guide the airflow out of the housing.

Abstract: The present invention relates generally to propulsion systems and, more specifically, to propulsion systems configured to vector and provide directional thrust such as those that may be used in aircraft or watercraft. Such propulsion systems may be used in connection with unmanned aerial vehicles, other aircraft, or various watercraft including submersibles.

Abstract: A satellite dispenser is disclosed. In various embodiments, a satellite dispenser as disclosed herein includes a dispenser body defining an interior cavity configured to receive a payload; and a composite guide rail comprising a groove configured to receive at least a portion of a payload, the composite guide rail having an orientation that substantially aligns a longitudinal axis of the groove with an ejection axis of the dispenser.

Abstract: A UAV body and a delivery structure, wherein the delivery structure has a mounting piece, a reset assembly and a limiting piece. The reset piece deforms when the piece to be transported is lifted, which resets to drive the piece to leave the mounting groove when the piece to be transported touches the ground. The first end of the limiting piece is connected to the reset piece, and when the piece to be transported is not lifted, the second end of the limiting piece can be connected to the mounting piece by magnet to seal the opening of the mounting groove. The reset piece drives the limiting piece to move so as to separate the second end from the mounting piece when the piece to be transported is lifted.

Abstract: An aircraft is provided. The aircraft includes a body having a seat adapted for a user to sit atop, a set of propulsion units for providing lift to the aircraft, and a steering mechanism for controlling movement of the aircraft. The steering mechanism includes a set of handlebars adapted for the user to grasp while sitting atop the seat. The steering mechanism also includes a steering column that is rigidly connected to the set of handlebars, where the set of handlebars and the steering column are rotatable about a longitudinal axis of the steering column. The steering mechanism further includes one or more sensors for detecting rotation of the steering column. The steering mechanism enables the user to control a yaw of the aircraft by turning the set of handlebars about the longitudinal axis of the steering column.

Abstract: Described here are multicopter systems and methods of operating multicopter systems, including those with a chassis with at least two mounted lift motors and at least four mounted control motors mounted within the chassis, wherein, the at least two mounted lift motors each having a lift propeller, the at least four mounted control motors each having a control propeller, wherein the lift propellers and the control propellers are in parallel planes or coplanar, a computer mounted on the chassis, the computer in communication with the control motors, an electric power source mounted on the chassis, the electric power source connected to the control motors, and an antennae mounted on the chassis, in communication with the computer. In some examples, the control systems are encrypted.

Abstract: A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.

Abstract: Aspects relate to an electric aircraft having a two-motor propulsion system and methods for use. An exemplary electric aircraft includes a flight component attached to the electric aircraft, where the flight component is configured to generate thrust, a first electric motor and a second electric motor, where each of the first electric motor and the second electric motor are mechanically connected to the flight component and configured to provide motive power to the flight component, and the second electric motor is able to provide motive power to the flight component if the first electric motor is inoperative.

Abstract: An unmanned aerial vehicle includes a fuselage defining a fuselage chamber. A first boom is coupled to the fuselage. A first rotor lift assembly is coupled to the first boom for providing a first lifting force. A second boom is coupled to the fuselage. A second rotor lift assembly is coupled to the second boom for providing a second lifting force. A third boom is coupled to the fuselage. A third rotor lift assembly is coupled to the third boom for providing a third lifting force. A fourth boom is coupled to the fuselage. A fourth rotor lift assembly is coupled to the fourth boom for providing a fourth lifting force. An electronic controller system is within the fuselage and operates the first rotor lift assembly, the second rotor lift assembly, the third rotor lift assembly and the fourth rotor lift assembly.

Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: Systems are described for transporting organic material, such as trees and logs, by flight. Such a transportation system may include a remotely-piloted air vehicle, a frame coupled thereto, multiple air vehicles, one or more propellers, a harness, and/or other components. The frame is coupled to both the remotely-piloted air vehicle and to the multiple other air vehicles.

Abstract: A hover-capable flying machine such as a drone includes a robotic arm extending from the body, and an instrumentality for balancing the machine in response to disturbances such as those caused by picking up and dropping of the payload by the extended robotic arm. In embodiments, the end of the arm is equipped with a balancing rotor assembly that may provide lift sufficient to counteract the weight of the payload and/or of the arm. In embodiments, the machine's power pack is shifted in response to the disturbances. The power pack may be moved, for example, on a rail within and/or extending beyond the machine in a direction generally opposite to the extended arm. The power pack may also be built into a bandolier-like device that can be rolled-in and rolled out, thus changing the center of gravity of the machine.

Abstract: An implementation of a contoured class divider for dividing an aircraft cabin includes a panel positioned between an aft seat and a forward seat, the panel having an aft-facing convex contour closely matching an aft-facing contour of a seatback of the forward seat and configured to enhance space utilization. The contoured class divider may include an articulation system to articulate at least a portion of the panel from a first position (normal operation) to a second position (emergency landing). The contoured class divider may provide up to an additional 12 inches of space which can be used to reduce seat pitch (and thereby enhance passenger comfort) or increase the number of rows of seats on a given aircraft.