Abstract: The present invention ensures that when condensation forms in a container for a flying object, water from the condensation does not adversely affect an object in the container. Container 12 is a cabin of a gas balloon and comprises Main Body 121, which is an airtight container for accommodating Crew Member H1 and is filled with Air 122, Condensation Promoting Member 123 is made of a material that has a high thermal conductivity, such as aluminum, and is partly exposed to the inside of Main Body 121 and partly exposed to the outside of Main Body 121. Water Collecting Vessel 124 is positioned below the portion of Condensation Promoting Member 123 exposed to the inside of Main Body 121 and collects water from condensation formed on Condensation Promoting Member 123. Conduit 125 directs water collected by Water Collecting Vessel 124 to Water Collection Container 126.

Abstract: Exemplary inventive practice improves the taxiing dynamics of a seaplane by propulsively imparting roll moments so as to continually encourage levelness of the two wings, thereby maintaining both wings completely above (out of) the water. Two matching motor-driven propellers are correspondingly positioned at or near the wingtips. A computer receives sensory motion inputs and transmits sequential commands that continually adjust the respective propulsive forces of the wingtip propellers by effecting equal and opposite changes in their respective rotational speeds. An increase in one wingtip propeller's rotational speed is concomitant a decrease in the other wingtip propeller's rotational speed, wherein the increase and the decrease are of the same magnitude. The seaplane rolls upward on the wing whose wingtip propeller is increasing in rotational speed. Control of the seaplane's rolling motion is thus enabled by a sustained propulsive equilibrium between the two wingtip propellers.

Abstract: Embodiments of the present application are a UAV foot stand and a UAV. The UAV foot stand includes a main body, a mounting board, and a support structure, where one end of the main body is provided with a lightening cavity, one end of the main body that is provided with the lightening cavity extends outward to form the mounting board, the support structure is fixed to the main body, and the support structure at least partially extends into the lightening cavity and is connected to an inner wall of the lightening cavity, so as to increase rigidity of the main body.

Abstract: A wing drop fuel tank it is provided comprising a rigid external casing 1 and a second tank 2 arranged inside said rigid casing 1, said second tank 2 being made of flexible material. A production process of said wing drop tank it is also provided which comprises the following steps: construction of two rigid half-shells 10 and 11, and the subsequent mutual coupling of the former creates a single rigid structure 1; making of a first port and a second port at the upper part of the half-shell 10, said second port having same size of a fuel filling flange 23 on said tank 1; inserting of a second tank 2 made of a flexible material through said first port in said first tank 1; and applying a closing plate 12 at said upper port, said closing plate 12 being removably locked on said tank 1 by means of clamping screws 13 which engage with threaded holes 22 made on a flange 21 integral with said second tank 2.

Abstract: The invention relates to an aircraft (1).

Abstract: Methods, Systems, and Apparatus for coordinating drones to communicate with reduced signal to noise, harvest energy, or provide camouflage.

Abstract: Aspects of the present disclosure are related unmanned aerial vehicles tethered to ground stations with an expendable airborne fiber-optic link. The tethers may be fiber-optic cables that can be used as a communications conduit between a ground station and a UAV for providing vehicle positioning/control information to the UAV as well as transmitting a large amount of information/data to the UAV. As the information being transmitted between to the UAV the ground station is critical, fiber-optic cables provide the bandwidth and transmission capabilities required with the added benefit of electromagnetic interference (EMI) and radio-frequency interference (RFI) immunity, making this an ideal solution for these applications.

Abstract: Systems and methods for a gyroscopic rotational wing for an aircraft are disclosed. In one embodiment, a safety and stability device for an aircraft comprises an inner ring, an outer ring that rotates relative to the inner ring, and a motor connected to the inner ring that drives rotation of the outer ring relative to the inner ring. In some embodiments, the safety and stability device rotates in a substantially horizontal plane and at a rotational speed sufficient to provide gyroscopic stability for the aircraft.

Abstract: A berley dispenser, including a container to store berley, a homogenizer within the container to form a homogenized berley from one or more predetermined homogenized berley settings where each setting corresponds to a particular fish type, a discharge port to discharge the homogenized berley, and a controller to control the homogenization of the berley by the selection of the one or more predetermined homogenized berley settings to form the homogenized berley and control the discharge of the homogenized berley. The controller can communicate with a GPS navigator, fish finder or other similar device to coordinate the homogenization of the berley and/or discharge of the homogenized berley.

Abstract: Embodiments of a payload attachment system secure a payload to a wing or fuselage of the drone 102 (or another type of aircraft) using one or more vacuum mounting modules, wherein each vacuum mounting module comprises at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives an instruction corresponding to one of a vacuum cup actuation signal or a vacuum cup release signal.

Abstract: A self-propelled payload (SPP) for an aircraft, such as an unmanned aircraft. The SPP includes an independent propulsion unit which is configured to counter the effect of payloads of the aircraft. This improves operational effectiveness of the aircraft.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: receiving, via the processor, an ejection command for ejecting an ejection seat from an aircraft; determining, via the processor, an aircraft or ejection seat altitude and an aircraft or ejection seat speed; and commanding, via the processor, a simultaneous or staged deployment of a drogue parachute and a main parachute upon or just prior to separation of the ejection seat from the aircraft, the simultaneous or staged deployment being described herein.

Abstract: An ejection seat may comprise a seatback, a headrest located at an upper end of the seatback, and a pitot tube rotatably coupled to the headrest. A pitot restraint assembly may be operably coupled to the pitot tube. The pitot restraint assembly may be configured to translate between a restrained state and a released state. The pitot tube may rotate from a stowed position to a deployed position in response to the pitot restraint assembly translating to the released state.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes an aircraft control surface. The aircraft control surface includes a first skin, a second skin and a support structure laterally between and connected to the first skin and the second skin. The support structure includes a spar, a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface. The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface to the spar. An actuator receptacle projects longitudinally into the aircraft control surface from a base of the aircraft control surface to the spar. The actuator receptacle extends spanwise within the aircraft control surface between the first stiffener and the second stiffener.

Abstract: The technology relates to techniques for drogue deployment for a lighter than air (LTA) vehicle descent. A drogue deployment system for an LTA vehicle descent can include a drogue comprising a drogue parachute coupled to a carrier. A spring can be configured to launch the drogue from a launch tube directed outward from an apex of the LTA vehicle in an acute angle from a horizontal plane. A core can be placed around the launch tube and placed around the spring, the core compressing the spring and holding the spring in a compressed state prior to deployment, and a riser can couple the carrier to the envelope of the LTA vehicle. In some cases, the drogue deployment system can comprise two or more drogues, wherein intervals between the two or more drogues can be selected such that horizontal components of drogue deployment forces approximately cancel out.

Abstract: A single acting actuator for an aircraft landing gear assembly is disclosed having a piston mounted in a cavity and moveable relative to a housing between a retracted position and an extended position, the piston dividing the cavity into first and second pressure chambers. At least one of the pressure chambers is associated with first and second outlets, with the actuator being arranged such that, in respect of the relative movement in which the pressure chamber is the decreasing volume pressure chamber, in a first stage of the relative movement the first and second outlets are open thereby allowing actuator fluid to flow out of the pressure chamber through the first and second outlets and in a second stage of the relative movement the second outlet is open but the first outlet is closed, thereby acting to slow the relative movement of the piston with respect to the housing.

Abstract: A method and system for preparing a distribution program for insects comprises obtaining distribution data of a wild population of insects; obtaining distribution parameters including distribution resolution levels of at least one available distribution vehicle; generating a population density map at a resolution level consistent with the distribution resolution level of the vehicle; generating a release map by modifying the population density map in accordance with the distribution parameters; and generating a path using the release map, the path defining dosages of insects to be released at respective locations along the path.

Abstract: The present technology relates to an unmanned aerial vehicle, a drive method, and a program that make it possible to easily balance an airframe. An unmanned aerial vehicle includes: a plurality of motors that rotates a plurality of propellers; a movable part that moves a center-of-gravity position adjustment member; and a control unit that controls movement of the center-of-gravity position adjustment member by the movable part. The present technology can be applied to unmanned aerial vehicles.

Abstract: The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

Abstract: An aerial robot system may include an aerial robot having an airframe, a piezo actuator, a wing connected to the piezo actuator, and a photovoltaic cell. The system may further include a laser source configured to emit a laser beam oriented toward the photovoltaic cell for conversion by the photovoltaic cell into electrical energy. The aerial robot may further include a boost converter connected to the photovoltaic cell and configured to raise a voltage level of the electrical energy, and a signal generator connected to the boost converter and configured to generate an alternating signal. The piezo actuator is connected to the signal generator to move according to the alternating signal to cause the wing to move in a flapping motion to generate aerodynamic force that moves the robot. Methods for manufacturing aerial robots and corresponding electronics are also disclosed herein.