Abstract: A guided missile with a sleeve-shaped missile body, at least one engine for producing forward thrust, at least one flight direction control device, and at least one aerodynamic extension. The least one flight direction control device is rotatably mounted to a top area and/or a bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The least one aerodynamic extension comprises an aerodynamic cross-sectional shape that is arranged on a left-hand side and/or a right-hand side of the sleeve-shaped missile body.

Abstract: A system for initiating a canopy release signal for a canopy of an aircraft includes a first striker secured to the canopy, and a first initiator assembly secured to a fuselage of the aircraft. The first initiator assembly has a protrusion. The first striker is configured to be rotated against the protrusion of the first initiator assembly. The canopy release signal is output in response to the first striker rotating against the protrusion of the first initiator assembly.

Abstract: A method for realizing a vertical take-off and landing aircraft that does not use a mechanism dedicated for take-off and landing, which cannot be achieved on the basis of an existing concept of aircraft flight control, by introducing a new concept of a shoulder rotational axis and an arm rotational axis into aircraft flight control and controlling vertical take-off and landing and ordinary flight with the same mechanism. This instruction eliminates a necessity of a tail and ailerons from an airframe of the aircraft, enables reduction of manufacturing, maintenance, and running costs thereof, and makes it possible to avoid problems of maneuverability and cruising distance performance of airframes of vertical take-off and landing aircrafts.

Abstract: There is disclosed in one example a tiltrotor system for a vertical takeoff and landing (VTOL) aircraft, including: a rotor pylon, wherein the rotor pylon is rotatable, via a rotation maneuver, between a substantially horizontal orientation and a substantially vertical orientation; a linear actuator disposed to actuate the rotation maneuver; and a mechanical guide disposed to maintain a center of gravity along a substantially linear axis throughout the rotation maneuver.

Abstract: Aircraft propulsion and torque mitigation technologies for aircraft are described. In embodiments, the disclosed technologies enable the provision of rotational torque for rotating the rotor blades of a vertical lift aircraft, while mitigating or even eliminating the need for counter torque methods and apparatuses such as tail rotors and counter rotating blades.

Abstract: Embodiments of the present invention provide a novel deterrent barrier based on the phenomenon of fluid cavitation. A drive unit comprising a motor and a propeller are configured for inducing cavitation in water. The cavitation takes the form of a rotationally confined vertical column of cavitation bubbles extending from the propeller, and a one-dimensional series of drive units spanning the width of a waterway may provide an effective, environmentally friendly and non-lethal barrier against entry of target fish species.

Abstract: A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

Abstract: A pylon conversion actuator, for use in tiltrotor aircraft, that converts the tiltrotor between hover flight mode and forward flight mode. Pylon conversion actuator selectively retracts and extends between a retracted position to an extended position. Pylon conversion actuator includes an extendable arm, a motor, and an actuator platform.

Abstract: A supporting device on a supporting pole, in particular for at least one wire for containing row, which includes wire-holding element formed by shaped thread-like body comprising resting portion adapted to be removably rested, in use, on first portion of outer surface of supporting pole and supporting means for containment wire extending from opposite sides with respect to resting portion, and pulling and anchoring element formed by shaped thread-like body including engagement portion adapted to interact, in use, with second portion of outer surface of supporting pole opposite to first portion and elastically deformable anchoring means which extend substantially perpendicularly and from opposite sides with respect to engagement portion and adapted to cooperate with second portion of outer surface of supporting pole.

Abstract: A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

Abstract: Provided is a device for flipping or rotating a floating aquatic cage to mitigate biofouling, and for farm management, such as to carry out maintenance and facilitate harvesting, particularly the style of floating cage used in farming oysters and other shellfish. The device includes a hollow frame or housing which defines a path through which the floating aquatic cage may pass, including entrance and exit openings; and one or more guide elements positioned on an inside surface of the hollow frame or housing. The one or more guide elements form an obstruction to opposing corners of the floating aquatic cage, and impart a turning force in such a manner as to rotate the floating aquatic cage.

Abstract: Spacecraft servicing devices and related methods may include a propellant tank configured to store a propellant and to be placed into fluid communication with a portion of the target spacecraft.

Abstract: A conversion system for a tiltrotor aircraft may be configured to control tilting of a pylon assembly relative to a wing of the aircraft. The system may include a means for generating asymmetric thrust with a propulsion rotor carried by the pylon assembly to generate a first torque on the pylon assembly in a first direction. The system may include a brake mechanism to selectively resist the first torque on the pylon assembly by applying a second torque to the pylon assembly in a second direction opposite the first direction. The rotor (via asymmetric thrust generated by the rotor) and the brake mechanism are coordinated to work against each other to control the tilt rate and angle of the pylon assembly during conversion between flight modes of the tiltrotor aircraft. Other aspects of the present technology include methods of tilting rotors of tiltrotor aircraft using asymmetric thrust and brake mechanisms.

Abstract: A handle assembly for an access panel is described and includes a support structure including upper and lower supports attached to the access panel, each of the upper and lower supports comprising a top face and a bottom face; a handle for selectively engaging with the support structure, the handle comprising a grip portion and upper and lower flanges extending perpendicularly from the grip portion, each of the upper and lower flanges comprising a top face; and a retention mechanism for retaining the handle in contact with the support structure with a combination of magnetic and mechanical force.

Abstract: Systems and methods are disclosed for servicing objects such as a launch vehicle or an aircraft with an elevated platform that conforms to differently sized and shaped objects. The platform can have telescoping planks that extend to conform to the outer surface of the object. Glide pads with low friction surfaces, rollers, etc. can reduce the friction between a plank and a supporting surface and between adjacent planks such that planks can be manually moved into position. In addition, the plank holders can limit the planks to a linear movement, secure the planks to a supporting surface, and control the friction force between the planks and the supporting surface. Further still, the supporting surface can be a carrier and/or a support that moves the planks closer to the object and tilts the planks out of the way so that an object can be positioned within the platform.

Abstract: A propulsion assembly for a rotorcraft includes a raceway having a tapered inner surface and a mast configured to receive the raceway at a raceway receiving station. The mast has a tapered outer surface at the raceway receiving station. The propulsion assembly includes a mast bearing assembly having a plurality of bearings facing the mast to engage the raceway. The tapered inner surface of the raceway is friction welded to the tapered outer surface of the mast at the raceway receiving station to form a tapered friction weld line.

Abstract: The main objective of this invention is to improve the efficiency and service life of a rubber tree rain guard seal. The performance of existing rubber tree rain guard seals depends on a fixed mechanical and or chemical attachment of the seal to the tree. These methods of attachment prevent the seal from expanding with the circumferential growth of the tree resulting in premature seal failure and damage to the tree within a year of operation. In this invention the seal is comprised of five components that are not fixed to the tree, allowing the seal to expand along with tree growth. An adjustable outer seal connector regulates the pressure required to establish consistent sealing contact against the tree, thus providing extended service life of the seal assembly. The seal assembly comes apart for easy maintenance.

Abstract: An airship includes a gasbag, a cockpit and a first shaft body, where the gasbag is filled with a gas for lifting the airship; the gasbag and the cockpit are sequentially arranged along an axial direction of the first shaft body and fixed to the first shaft body, and there is a spacing between the gasbag and the cockpit; at least one of the gasbag and the cockpit is rotatably connected to the first shaft body; after the gasbag is filled with the gas for lifting the airship, any section of the gasbag in a direction perpendicular to the axial direction of the first shaft body is circular or annular; and the axial direction of the first shaft body is the same as a direction of gravity.

Abstract: A rotorcraft, and, more particularly, to a rotorcraft with a fuselage having a center line, at least one main rotor that generates vortices during operation, and a stabilizer wing, whereby the stabilizer wing has a planform that reduces the unsteady aerodynamic loads caused by the wake of the at least one main rotor. In particular, the stabilizer wing may be provided with a left wing tip, a right wing tip, a quarter chord line with a non-zero curvature, such that an interaction between the vortices generated by the at least one main rotor and the quarter chord line is spread out over time, a leading edge that is arc-shaped, and a trailing edge that is arc-shaped.

Abstract: A device (10) for trapping and killing marine organisms (14) such as animal plankton, salmon lice and other parasites, comprises a body (12; 12?) configured for submersion in water (15). The body (12; 12?) comprises at least one light source (16) configured and controlled for attracting said marine organisms, and an internal cavity (20) having an opening (20?) for fluid communication with at least a portion of the water. The light sources (16) are arranged inside the cavity (20) and arranged and controlled to emit light waves through said opening and into at least a portion of the water. At least one positive electrode (24; 24?; 24?; 32) is arranged in the cavity and electrically connected to a low-voltage power source (26; 27; 30), and at least one negative electrode (15a) is arranged in the water and electrically connected to said power source (26; 27; 30).