Abstract: A field incinerator has a carriage with a frame. A fuel tank such as a propane tank is mounted to the frame. An outlet passage extends from the tank. An outlet valve is mounted to the outlet passage. The outlet valve controls the outlet passage. The first gauge has a first gauge tap. The first gauge tap is connected to the fuel tank or the outlet passage. The first gauge has a first gauge control parameter. The first gauge control parameter requires less than a first set pressure for activation. The second gauge is connected to the outlet passage downstream from the first gauge. The second gauge has a second gauge control parameter. The second gauge control parameter requires more than a set second pressure for activation. The first gauge control parameter and the second gauge control parameter must both be fulfilled for opening the outlet valve.

Abstract: An actuation system for an aircraft piston engine includes a controller and an actuator. The controller selectively supplies motor control signals to a motor. The actuator includes a housing, a motor, a main rod, a control handle, and an inner rod. The main rod receives a drive torque from the motor and translates in either a first axial direction or a second axial direction. The main rod is responsive to an axial drive force to translate in either the first axial direction or the second axial direction. The inner rod is disposed within the main rod and is movable between a first position, in which main rod rotation causes the main rod to translate, and a second position, in which main rod rotation does not cause the main rod to translate, but application of the axial force to the control handle causes the main rod to translate.

Abstract: A modular flat-packable drone kit includes a plurality of components that can be assembled into a drone. Components of the drone kit include elements that may be cut from a flat sheet of material, thereby enabling low cost manufacturing and compact packaging and may be assembled without specialized tools. A set of drones may operate in a standalone mode or may be coupled together and operated in a group configuration.

Abstract: A propulsion assembly including a primary structure of a pylon having right and left extensions projecting with respect to right and left lateral panels of the primary structure and also right and left brackets, each having a first flank connected to the right or left lateral panel of the primary structure and a second flank pressed against the right or left extension, a front engine mount having first and second links, each connected to an engine and directly to the front transverse reinforcement by a first or second reinforcement connection pin passing through the right or left extension and the second flank of the right or left bracket.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a composite structure, an integral bearing comprising a first frustoconical portion and a second frustoconical portion each having a complimentary shape to the composite structure, a sleeve comprising a third frustoconical portion coupled to a cylindrical bearing surface of the integral bearing, and a metallic end fitting coupled to the third frustoconical portion, wherein the metallic end fitting comprises a bearing portion contacted with the cylindrical bearing surface.

Abstract: Fuel tank inerting systems are described. The systems include a fuel tank, a catalytic reactor arranged to receive a reactant mixture comprising a first reactant and a second reactant to generate an inert gas to be supplied to the fuel tank to fill an ullage space of the fuel tank, a condenser heat exchanger arranged between the catalytic reactor and the fuel tank and configured to cool an output from the catalytic reactor, and a fan assembly arranged within an inerting system flow path upstream of the catalytic reactor, wherein the fan assembly is arranged within a gas flow having a temperature of at least 185° C.

Abstract: A method for remedying sandy land by using a simulated loam substrate spray-seeding technology includes: first, carrying out a sand-fixing treatment to lay a metal mesh in sandy land, the metal mesh being fixed to the surface of the sandy land by a sand-fixing pile; second, spray-seeding a seed into the sandy land by simulated loam substrate spray-seeding; and finally, after spray-seeding, carrying out maintenance management, including adding a protective plate around the metal mesh, covering with a non-woven fabric, watering, fertilizing, reseeding, and post-monitoring. The present invention adopts a two-layer spray-seeding method, and rapidly simulates a loam substrate suitable for plant growth by bionics; the simulated loam substrate having good water retention capacity (conducive to a higher germination rate of seed), root development, microbial activity, nutrient transformation, and plant growth and development. With less investment and having a quick effect, large-scale sand control is provided.

Abstract: [Object] To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. [Solution] The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.

Abstract: An aquaculture system (1) for farming aquatic organisms includes an apparatus (2) for supplying oxygenated water into an enclosure (20) in which aquatic organisms are to be fanned. The apparatus (2) includes a water inlet (4) and an oxygen inlet (6) to create a water and oxygen mixture. The apparatus (2) also includes a venturi (17) arranged to dissolve the oxygen into the water passing through the venturi and such that the oxygen and water mixture passing through the venturi (17) is exposed to a substantially null magnetic field. The apparatus is also arranged such that the water and oxygen mixture that is supplied to the venturi (17) contains substantially no colloidal minerals. The apparatus also includes an outlet (18) for the oxygenated water in fluid communication with, and downstream of, the venturi (17) and in fluid communication with the inlet of the enclosure (20).

Abstract: Various embodiments for a foldable quad-rotor (FQR) inspired by an origami mechanism are disclosed herein. The FQR can fold its arms during flight to enable aggressive turning maneuvers and operations in cluttered environments. A dynamic model of folding is built for this system with the collected data, and a feedback controller is designed to control the position and orientation of the FQR. Lyapunov stability analysis is conducted to show that the system is stable during arm folding and extension, and motion planning of the FQR is achieved based on a modified minimum-snap trajectory generation method.

Abstract: An emergency exit door (2) for an aircraft cabin, the door includes an opening-assist mechanism and an opening/closing device having a control lever (7), which can selectively be actuated to either unlock the door (2) and permit the action of the door (2) opening assist mechanism or to lock the door (2). The control lever (7) includes an adaptation mechanism (10) for adjusting the lever arm, the adaptation mechanism (10) being moveable between at least two positions: an opening-action position and a closing-action position, the lever arm (LO) of the control lever (7) in the opening-action position being shorter than the lever arm (LF1, LF2) of the control lever (7) in the closing-action position.

Abstract: Container retention and release apparatus are disclosed. An example container retention and release apparatus includes an actuator and a swaybrace and retention assembly pivotally coupled to the actuator. The swaybrace and retention assembly is to pivot relative to the actuator between a first position to retain a container and a second position to release the container. The swaybrace and retention assembly includes a swaybrace arm having a receptacle to engage a post of a container. The swaybrace arm to pivot between the first position to cause the receptacle to engage the post of the container to retain the container and the second position to cause the receptacle to disengage the post to release the container.

Abstract: A removable step assembly for a helicopter includes a main tube, which supports a forward step and a rear step, as well as a bushing housing. The main tube is mounted to a helicopter by the bushing housing, an associated bushing, and by an adapter assembly that is secured to the cabin of the helicopter.

Abstract: Described herein are compositions and methods relating to functionalized sands or soils.

Abstract: An adapter plate for an aircraft seat may include a body configured to be positioned exterior of an armrest of the aircraft seat within a space proximate to the aircraft seat. The body may include at least one coupler configured to attach to the aircraft seat. The body may include at least one mount point. The at least one mount point of the body may be configured to attach to at least one mount bracket of the removable auxiliary aircraft accessory. The auxiliary aircraft accessory may be positioned within the space proximate to the aircraft seat when coupled to the at least one mount point of the body via the at least one mount bracket.

Abstract: A first deployment mechanism (30) deploys a first radiator panel (20) from a state where the first radiator panel (20) is opposed to a north or south face (10) of the body structure of a satellite. A second radiator panel (40) is stacked with the first radiator panel (20) to be opposed to the north or south face (10) of the body structure of the satellite and is sandwiched between the north and south face (10) of the body structure of the satellite and the first radiator panel (20), in a state where the first radiator panel (20) is opposed to the north or south face (10) of the body structure of the satellite. A second deployment mechanism (50) connects the second radiator panel (40) to the north or south face (10) of the body structure of the satellite, and deploys the second radiator panel (40) in a direction P2 opposite to a deployment direction P1 of the first radiator panel from a state where the second radiator panel (40) is opposed to the north or south face (10) of the body structure of the satellite.

Abstract: Proposed are a shell launcher for a drone and a method of launching shells for a drone. According to the shell launcher for a drone and the method of launching shells for a drone, by launching shells such as EFPs using a drone, it is possible to use a drone as various weapon systems.

Abstract: An electronic aircraft control system and an electronic aircraft control method are provided. In some embodiments, the aircraft control system includes a motor including a rotating shaft, a lever including an axis of rotation, the lever connected to the rotating shaft, wherein the position of the lever is not maintained by a mechanical clutch during normal operations. In some embodiments, the aircraft control system includes a fail-safe system for maintaining mechanical friction of the lever in an event of a failure, a sensor identifying a position of the lever, and a transmitter transmitting the lever position to a controller, the controller adjusting an aircraft performance device based on the received lever position. In some embodiments, the motor provides a torque on the lever. In some embodiments, the fail-safe system includes shear pins configured to break when a sufficient amount of manual torque is applied to the lever.

Abstract: A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.

Abstract: A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed. The power management system includes a first engine that provides a first power input to the main rotor system. A second engine selectively provides a second power input to the main rotor system. The second engine has at least a zero power input state and a positive power input state. A power anticipation system is configured to provide the first engine with a power adjustment signal in anticipation of a power input state change of the second engine during flight. The power adjustment signal causes the first engine to adjust the first power input to maintain the main rotor speed within a predetermined rotor speed threshold range during the power input state change of the second engine.