Abstract: A rotor-regulation system includes a rotor comprising a plurality of blades, a mechanically driven hydraulic pump, a rotor drive shaft operable to drive the rotor and the mechanically driven hydraulic pump, and a throttling valve coupled to the mechanically driven hydraulic pump and operable to modulate rotation of the rotor.

Abstract: A nose-wheel steering system may comprise an actuator and a bevel gear rotationally coupled to a drive shaft of the actuator. The bevel gear may be configured to rotate about a first axis. A collar gear may be intermeshed with the bevel gear. The collar gear may be configured to rotate about a second axis that is generally perpendicular to the first axis.

Abstract: The disclosed propulsion system of a space vehicle and the methods of operating the propulsion system use a microwave energy source to heat propellant in a propellant chamber that pierces and traverses a waveguide carrying the microwave energy. In some implementations, the microwave energy ionizes and further heats the propellant in the propellant chamber. The partially ionized and heated propellant may exit the propellant chamber via a nozzle to generate thrust.

Abstract: A system for use with a tripod landing gear assembly of an aircraft may comprise: a tension strut assembly having a tension strut extending from an upper end to a lower end; a drag brace assembly having an upper brace and a lower brace, the upper brace pivotably coupled to the lower brace at a center point, the lower brace rotatably coupled to the lower end of the tension strut; and a jury linkage pivotally coupled to the drag brace assembly at the center point rotatably coupled to a middle portion of the tension strut, the middle portion between the upper end and the lower end.

Abstract: Disclosed is an unmanned aerial vehicle adapted to be positioned against a substantially vertical wall while hovering in the air, including a body and rotors, an arm end, a first leg end and a second leg end intersected by a front plane and adapted for together contacting the wall at three spaced apart positions, the front plane intersecting a vertical axis of the UAV at an upper side of a first plane spanned by a lateral and longitudinal axis of the UAV, the front plane extending at a first angle of between 45 to 85 degrees to the first plane; wherein the UAV is adapted for tilting upon contact of the first and second leg ends with the wall while the arm end approaches the wall, about the first and second leg ends and towards the wall, until the arm end contacts the wall.

Abstract: The present invention concerns a landing gear (1) for a light aircraft, i.e. weighing less than 5.7 tonnes, the landing gear consisting of at least one wheel (3) attached to a chassis or to a fuselage of the aircraft by means of a connecting element (2). According to the invention, the wheel (3) is connected to the connecting element (2) via a system (4) of two damping cylinders arranged between the wheel (3) and the connecting element (2).

Abstract: A noise reduction apparatus, an aircraft, and a noise reduction method capable of increasing the amount of noise reduction are provided. The noise reduction apparatus 1 includes a porous plate 2 disposed to face a fluid flow, the porous plate 2 including a bend region 5 bent toward an upstream side of the fluid flow. The bend region 5 is provided at the end portion 6 of the porous plate 2, and has a concave R-shape on an upstream side of the fluid flow.

Abstract: Presently disclosed subject matter integrates a method of using thousands of semi-autonomous unmanned aerial vehicles, herein called drones, to deliver vastly superior amounts of fire retardant over substantially larger and variably-shaped drop patterns. Each drone is able to swap its own batteries with freshly charged batteries and each drone is able to refill its container with water or fire retardant. Once launched, a swarm of drones can perform repeated trips from the water/retardant source to the fire without human involvement other than the high-level tasking of where to drop the retardant. Once a general drop destination and drop pattern shape is designated, the swarm can transport retardant to that location, form itself into the desired drop shape, and deploy retardant. The drone body is designed to be modular so different components can be attached with ease and no special training or knowledge required.

Abstract: A center biased actuator having an outer cylinder, a slave cylinder linearly transposed within the outer cylinder, a rod assembly with a piston linearly transposed within the slave cylinder and a rod extending from the outer cylinder, one or more first dynamic seals arranged to act on a sidewall of the rod to inhibit hydraulic fluid leaking from the outer cylinder, one or more second dynamic seals arranged to act on a sidewall of the slave cylinder or an inner surface of the outer cylinder to inhibit hydraulic fluid leaking from the outer cylinder, and a gas chamber comprising a sealed expandable chamber containing gas. The expandable chamber is arranged to act on hydraulic fluid within the center biased actuator to bias the center biased actuator to assume an intermediate condition which lies between a compressed condition and an extended condition.

Abstract: Closure devices and methods are provided for closing a stringer penetration space defined between a stringer and a wing rib of an aircraft wing section. According to certain embodiments, the closure devices will integrally include a forward face plate positioned in covering relationship to at least a portion of the stringer penetration space, and a rearwardly projecting attachment arm rigidly adapted for rigid attachment to the stringer so as to positionally fix the forward face plate relative to the stringer penetration space.

Abstract: Winged tilt-rotor vertical take-off and landing (VTOL) aircraft and related methods are disclosed. Aircraft comprise an airframe comprising one or more wings; one or more tilt-adjustable rotors positioned forward of the one or more wings; and one or more fixed-tilt rotors positioned behind at least one of the one or more wings. Methods comprise tilting only one or more forward rotors positioned in front of one or more wings of the aircraft, and not tilting one or more rearward rotors positioned behind at least one of the one or more wings.

Abstract: The present disclosure provides a truss strap integrated geometric restraint for an evacuation slide. The truss strap integrated geometric restraint may comprise a first strap configured to be coupled to a first portion of the evacuation slide, a second strap configured to be coupled to a second portion of the evacuation slide, and a third strap detachably coupled to a third portion of the evacuation slide and configured to disengage from the portion of the slide in response to a predetermined force acting on the release mechanism, wherein the truss strap integrated geo restraint is configured to increase beam strength of the evacuation slide.

Abstract: A balloon system including a balloon, a payload, and a safety module. A safety module, preferably including a tether and a parachute, and optionally including a cover and/or a drogue. A method of balloon system operation, preferably including operating the balloon system in flight and descending under a parachute.

Abstract: An aircraft landing gear is disclosed having a first oleo strut include a sleeve portion and a slider portion, the slider portion being slidable within a hydraulic fluid chamber of the sleeve portion, and a second, similar oleo strut. The landing gear also includes a hydraulic fluid balancer having a balance chamber separated into first and second end sections, wherein the hydraulic fluid chamber of the sleeve portion of the first oleo strut is fluidly connected to the first section of the balance chamber and the hydraulic fluid chamber of the sleeve portion of the second oleo strut is fluidly connected to the second section of the balance chamber of the hydraulic fluid balancer.

Abstract: An aircraft portion having a floor and a fuselage structure forming an arch above the floor is disclosed in which a monument is mounted within the fuselage. The monument is suspended from the fuselage structure by at least one suspension point, so that most of the weight of the monument is taken up by the fuselage structure. The monument includes a circular or a round section configured to take up the vertical forces than the horizontal floor, which bends under vertical loads.

Abstract: Techniques involve releasing and/or capturing a fixed-wing aircraft using an aerial vehicle with VTOL capabilities while the fixed-wing aircraft is in flight. For example, the VTOL aerial vehicle may take off vertically while carrying the fixed-wing aircraft and then fly horizontally before releasing the fixed-wing aircraft. Upon release, the fixed-wing aircraft flies independently to perform a mission (e.g., surveillance, payload delivery, combinations thereof, etc.). After the fixed-wing aircraft has completed its mission, the VTOL aerial vehicle may capture the fixed-wing aircraft while both are in flight, and then land together vertically. Such operation enables the fixed-wing aircraft to vertically take off and/or land while avoiding certain drawbacks associated with a conventional VTOL kit such as being burdened by weight and drag from the VTOL kit's rotors/propellers, mounting hardware, etc.

Abstract: A cooling duct configured to introduce air flow to a cooling target device provided in a helicopter body of a helicopter includes a duct body, a front opening, an upper opening, a hinge, and a movable blade. The duct body is mountable below a main rotor of the helicopter to be adjacent to the cooling target device. The front opening is formed on a forward side of the helicopter body in the duct body. The upper opening is formed on an upper side of the helicopter body in the duct body. The hinge is disposed in an upper portion of the duct body and includes a pivot shaft extending in a lateral direction of the helicopter body. The movable blade with an end that is pivotally supported by the hinge is provided to be pivotable about the pivot shaft between a first position and a second position.

Abstract: A vertical takeoff and landing aerial vehicle. A left linear support and a right linear support of the unmanned aerial vehicle are respectively provided with a first group of multiple lift propellers and a second group of lift propellers, and the aerial vehicle is provided with a left dorsal fin and a right dorsal fin. By arranging a plurality of lift propellers, a left dorsal fin, and a right dorsal fin on the vertical takeoff and landing aerial vehicle provided by the disclosure, the aerial vehicle is higher in stability in the flight process.

Abstract: Aspects of this disclosure relate to a custom aircraft door mounting system that employs a vertical rolling motion enabled assembly, comprising: a first fitting configured to be mounted to an overhead structure of an aircraft, the first fitting including a cam follower slot formed within the first fitting; an elastomeric bearing pivotally coupled to a second fitting; and a cam follower coupled to the elastomeric bearing, the cam follower being configured to slide vertically within the cam follower slot to accommodate relative motion between the second fitting and the overhead structure of the aircraft.

Abstract: A fixed-wing aerial underwater vehicle includes a shell component, a flight component and a pneumatic buoyancy component. The flight component includes a fixed wing and rotors, and the fixed wing and the rotors are mounted in the shell component. The pneumatic buoyancy component includes an air bladder and an inflation and deflation portion, and the inflation and deflation portion can inflate and deflate the air bladder. The air bladder is installed on the shell component, a containing space is formed in the shell component, and the inflation and deflation portion is partially or entirely installed in the containing space. Each rotor includes a rotor supporting rod, a motor base, a motor and a propeller, which are sequentially connected. A control method for the fixed-wing aerial underwater vehicle mentioned above is further provided.