Abstract: Drinking troughs for in particular poultry feature drinking valves arranged at regular intervals along a water supply line, with each drinking valve being assigned a water-collecting bowl (14). The water-collecting bowls (14) are usually made of plastic. The water-collecting bowls (14) are cleaned with agents that contain aggressive substances, which are capable of damaging the plastic of the water-collecting bowls (14). The invention is a water-collecting bowls (14) with a respective insert (17) made of a resistant material, thus making the water-collecting bowl (14) resistant to aggressive liquids, in particular cleansing agents.

Abstract: An attachable wing for an aircraft is disclosed. The attachable wing is configured to mount to the underside of the fuselage of an aircraft, such as a rotary wing aircraft (e.g., a helicopter) or a fixed wing aircraft. The attachable wing produces additional lift, which results in an increase in speed, and consequently, an increase in fuel efficiency and payload capacity. In some embodiments, the attachable wing is retractable to facilitate takeoffs and landings. Additionally, the apparatus may be made of a bulletproof or anti-ballistic material to protect the aircraft from incoming fire or crash damage. The airfoil apparatus provides additional lift, allowing for greater fuel efficiency and range of the aircraft on which it is installed.

Abstract: A platform for the aerial delivery of payloads into aquatic environments has a staged v cross-section formed by two walls extending from an end part. The portions of the two walls adjacent to the end part diverge from it at an angle ? and, together with the end part, form the tip of the platform. The remaining portions of the two walls, remote from the end part, form the body of the platform, and diverge at an angle ? that is greater than the angle ?. When the platform is deployed onto the surface of a fluid, it initially experiences a period of low deceleration as the tip penetrates the surface, followed by a period of higher deceleration, as the body contacts the surface.

Abstract: A tiltrotor aircraft having a fixed wing and tilting rotors has a rotor blade with a shaped tip portion that provides improved hover performance. The shaped tip portion preferably has a terminal anhedral of at least 20° with respect to its stacking line, and the blade has an overall twist from root to tip of at least 20°, and a thickness ratio between 19% and 30% at a radial station of 10%. These features advantageously conspire to provide a hover figure of merit of at least 0.84 and a cruise propulsive efficiency of at least 0.85. A controller preferably limits the rotor speed in sustained airplane-mode forward flight cruise of at most 40% of a hover maximum rotor speed, and alternatively or additionally limits a rotor edgewise advance ratio to at most 0.20.

Abstract: Using at least one pressure sensor in an emptying pipe or a feed pipe between emptying valves at the outlets from tanks and feed valves for feeding nozzles, to detect the pressure waves that result form opening and closing a feed valve, and then following operation of said valve, detecting the damping or disappearance of the pressure waves, indicating that the transition between the liquid propellant component and the pressurization gas is going past said pressure sensor, and thus that the tank is completely empty. This detection of complete emptying is a step in a method of managing propellant that makes it possible to allocate the remaining propellant to a residual lifetime for the satellite in orbit and/or to re-orbiting or de-orbiting the satellite.

Abstract: An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including a second outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension.

Abstract: A rudder of a commercial aircraft is provided that is divided along its longitudinal direction in at least one region and the parts of the rudder can be spread against the air flow surrounding the aircraft by means of an actuator in order to decelerate the aircraft.

Abstract: An insect trap (100, 200) having an entrapment chamber (110, 210) comprising one or more compartments, a tapered guide (130, 260) extending into each compartment, and an entry structure (120, 240) providing insect access to each compartment. The tapered guides optionally include a plurality of projections defining a crown structure for discouraging insect egress from the trap. The entry structures each define a plurality of entry apertures or entryways that are physically separated such that interactions between insects at different entryways is reduced or eliminated.

Abstract: A rib of an airplane wing is prevented from deforming due to a machining load when machining a rivet hole in parts where the rib and a skin are joined. With regard to a rib that provides a connection between first and second spars of the airplane wing, the rib is formed with mounting flanges secured to a skin via a rivet, a stringer through hole for a stringer to be positioned through, and first and second cutouts facing parts where the first and second spars and the skin are connected. Since reinforcing beads are formed along the mounting flanges and reinforcing flanges are formed so as to extend in the span direction from the edges of the stringer through hole and the first and second cutouts and be connected integrally to the mounting flanges, the stiffness of the rib toward a load in the vertical direction when drilling a rivet hole can be enhanced.

Abstract: The Longitudinal Flying Wing aircraft idea provides for design of large cargo and passenger aircraft in range from low to high subsonic and transonic speed. Such aircraft would have up to twice lower fuel consumption per unit of payload, higher lift capacity, and a significantly longer range, while having a significantly lower level of noise inside passenger cabin and cockpit relative to classical concept aircraft. This idea is further providing for efficient, reliable, and simple flight controls, hence it may be successfully applied for design of all-size, long range, high-lift-capacity unmanned aircraft throughout the entire range of subsonic speeds.

Abstract: An insect trap (100) with spaced apart first and second entry structures (120, 140), includes an entrapment chamber (100) having a first compartment (102) and a second compartment (104) separated from the first compartment with a transverse panel (106). A conical first tapered guide (126) extends from the first entry structure into the first compartment, and a second tapered guide (146) extends from the second entry structure to the second compartment. The guides encourage the target insects to venture further into the trap, while hindering egress from the trap. One or more of the compartments include means for retaining an attractant. Traps having more than two compartments with spaced apart entryways are also disclosed.

Abstract: A hybrid helicopter includes an airframe provided with a fuselage and a lift-producing surface together with stabilizer surfaces and a drive system including: a mechanical interconnection system between a rotor of radius (R) with collective pitch and cyclic pitch control of the blades of the rotor and at least one propeller with collective pitch control of the blades of the propeller; and at least one turbine engine driving the mechanical interconnection system. The hybrid helicopter includes first members for controlling the angle at which the at least one pitch control surface is set as a function of the bending moment exerted on the rotor mast relative to the pitch axis of the hybrid helicopter, and second members for controlling the cyclic pitch of the blades of the rotor in order to control the longitudinal trim of the hybrid helicopter as a function of flight conditions.

Abstract: A bird deflector and air replacement system for a jet engine, the bird deflector being conical or arcuate in shape as formed by suitable longitudinal and lateral interconnected bars, and the air replacement apparatus being one of a frustum or a selectively perforated tube or a modified cowl with cooperating external spaced-apart channels or openings formed therearound for directing additional air into the mainstream of the jet engine inlet. The system may be manufactured as an aftermarket add-on, or it may be manufactured as original cowl equipment for respective jet engine models.

Abstract: A harness for a quadruped animal including a chest strap which in use of the harness lies across the chest of the animal in front of the forelegs, the harness including an attachment for a leading strap, the attachment being slidably mounted on the chest strap for movement therealong. Each end of the chest strap is attached to a trunk loop which in use of the harness passes around the trunk of the animal behind the forelegs. The trunk loop includes a back strap which in use of the harness lies across the back of the animal affixed to a lower strap which in use of the harness passes under the animal behind the forelegs.

Abstract: Systems and methods for providing supplemental drag to an aircraft are disclosed. In one embodiment, a method includes detecting changes in at least one throttle resolver angle (TRA). Deflections are determined for one or more flight control surfaces based on the changes in TRA, and accordingly, the one or more flight control surfaces are deflected automatically to generate supplemental drag. The one or more flight control surfaces include at least one at least one of an aileron, a spoiler, and an elevator. Additionally, in one instance, the deflections of the one or more flight control surfaces is implemented as a rated limited time lag function of the changes in TRA.

Abstract: A window panel adapted for installation relative to a structure. The panel includes a single piece of generally transparent injection-molded material configured to span one or more openings in the structure. The panel has panel attachment inserts for attaching the panel relative to the structure. The inserts are embedded in the material alongside at least one edge of the panel. The panel has a curvature that essentially continues a curvature of the structure surrounding the opening(s) when the panel is installed relative to the structure. This panel can be single-pane and can provide an essentially continuous window along an aircraft fuselage.

Abstract: A structure for an aircraft comprises a first wall and a second wall. The first wall comprises two jackets of composite material disposed on either side of an intermediate arrangement and further includes at least one soleplate enabling it to be secured to the second wall. The structure further includes at least one elongate member extending facing the jacket and spaced apart therefrom, the elongate member being secured to the soleplate or to the second wall and being arranged to act as a bearing surface for a portion of the first wall that becomes separated from the soleplate after rupture.

Abstract: The present invention is a space launch system and method to propel a payload bearing craft into earth orbit. The invention has two, or preferably, three stages. The upper stage has rocket engines capable of carrying a payload to orbit and provides the capability of releasably attaching to the lower, or preferably, middle stage. Similar to the lower stage, the middle stage is a reusable booster stage that employs all air breathing engines, is recoverable, and can be turned-around in a short time between missions.

Abstract: Described is an animal containment system for containing an animal within a boundary, for maximizing the animal's usable area within the boundary, for not discouraging the animal from returning to within the boundary in the event the animal moves beyond the boundary, and for doing so without utilizing an independent polarity indicator. The animal containment system determines whether the animal is within the boundary or beyond the boundary by considering the polarity of an activation signal the animal containment system transmits from the boundary and receives at the location of the animal. The animal containment system determines the polarity of the activation signal by modulating the signal such that the modulation indicates the polarity of the activation signal. The animal containment system achieves the above-discussed features by delivering a stimulus to the animal only when it traverses the boundary from within the boundary.

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.