Abstract: A method and apparatus for aerial fire suppression utilizing a potable fire retardant chemical dispensing system, readily adaptable, without extensive aircraft modification, to various makes of aircraft, for dispensing current types of forest and range fire fighting chemicals. The aerial delivery system is self contained and reusable. It enables cargo/utility aircraft to carry and dump a load, under control. The aerial delivery system is capable of attachment at the wing box, pressurized delivery from the nozzles, and nozzles directed straight downward.

Abstract: An improved system for controlled aerial distribution of substances such as chemicals upon crops in a select field, including coordinating the simultaneous independent application of two different substances. The system may include a pair of sub-systems, one of which includes a computer controlling a variable flow valve capable of varying the release of a substance from the first subsystem. There may also be a second subsystem having a pump activated by a lever that also opens and closes the fluid communication of the first subsystem, in this basic version of the invention, manually positioning the lever to open the spray valve also commences continuous release of a second substance from the second subsystem at a constant rate, until the lever is positioned to close the first fluid communication.

Abstract: A drain-mast connector, for use in transportation vehicles such as aircraft, includes an interface pipe which extends through an outer skin of a fuselage of an aircraft via a nipple-like connector. Such a connector allows for simple plug connection of the drain mast pipe and allows less contamination of the fuselage due to grey water disposal. Such a plug-like connection does not require a complicated mounting process.

Abstract: Systems and methods for tracing aircraft vortices. One method includes directing a tracer from a first aircraft into a vortical flow generated by the first aircraft. The method can further include detecting a characteristic corresponding to the presence of the tracer directed into the vortical flow. Based at least in part on the detected characteristic, the method can include directing the flight of the first aircraft, or a second aircraft following the first aircraft, or both.

Abstract: Systems and methods for tracing aircraft vortices. One method includes directing a tracer from a first aircraft into a vortical flow generated by the first aircraft. The method can further include detecting a characteristic corresponding to the presence of the tracer directed into the vortical flow. Based at least in part on the detected characteristic, the method can include directing the flight of the first aircraft, or a second aircraft following the first aircraft, or both.

Abstract: An aerial application dispersal system that comprises an aerial vehicle and an aerial dispersal unit. The aerial dispersal unit provides an insect control substance, a flake auger, and a motor to drive the flake auger for transporting the insect control substance to a dispensing chamber. The aerial dispersal unit also provides a glue substance, a pump, and a motor to drive the pump for transporting the glue substance from a storage container to the dispensing chamber for mixing with the insect control substance. The dispensing chamber is provided with a motor for forcing the insect control substance mixed with the glue substance out an exit portal for disbursement over the designated area.

Abstract: Firefighting bucket (11) suspended from an aircraft by lines (15), has open top (12A) and a valve at base (13). The valve is attachable to the aircraft by remotely actuatable line (16) and independent movement of lines (15-16) may utilise the weight of the water to facilitate opening and closing of the valve. Dynamic sensing of a bucket attribute, e.g. weight, enables bucket (11) to be filled or discharged by a pre-determined volume by the pilot. Chemical fire retardant may be added by entraining it with water discharging from the valve.

Abstract: An aerially transportable tank (20) for storing a composition for discharging in flight, the tank including a neck (23) terminated by a composition discharge opening (24), and having a wall (21) extending the neck that is sufficiently deformable to be received in part or in full within the neck.

Abstract: Characterized in that in a first stage are loaded or produced on board in a mother aircraft at least a product or mixed of products to act on forest fires, pests or atmospheric phenomena; in a second stage the said product is stored in a glider container with gliding flight ability and equipped with a precision guidance system; in a third stage the glider container is dropped from the mother aircraft and guided towards the release point of the load; in a fourth stage the glider container releases of its interior the load of product on the release point, and in a fifth stage the glider container is recovered for a following reusing.

Abstract: Systems and methods for tracing aircraft vortices. One method includes directing a tracer from a first aircraft into a vortical flow generated by the first aircraft. The method can further include detecting a characteristic corresponding to the presence of the tracer directed into the vortical flow. Based at least in part on the detected characteristic, the method can include directing the flight of the first aircraft, or a second aircraft following the first aircraft, or both.

Abstract: An aircraft structural element having a cavity. The structural element has an opening in a wall of the cavity through which moisture located in the cavity can escape into the surroundings, wherein a drainage element for sealing the opening in the wall of the cavity is provided in the opening. In order that the structural element can be produced with a low expenditure on components and assembly equipment, the drainage element comprises a hollow cylinder which connects the cavity of the structural element to the surroundings, which is provided with an external thread having a predefined external diameter, and a head at one end which has a predefined diameter, wherein the external diameter of the thread is smaller than the head diameter.

Abstract: The invention relates to a deflector for an aircraft, comprising a discharge pipe for leading a fluid to be drained from the aircraft by way of an outlet end to the environment of the aircraft; an actuator, coupled to the discharge pipe, for swinging out, when required, the discharge pipe to at least one activation position, wherein in the activation position the outlet end is arranged so as to be spaced apart from the exterior skin of the aircraft, and the deflector guides the fluid to be drained so that it exits outside a flow boundary layer that is present on the exterior skin. The deflector according to the invention is activated when required and is able to discharge structure-damaging fluids to the environment in such a way that the exterior structure of the aircraft does not become wet, and at the same time the deflector according to the invention, normally accommodated within the contour of the aircraft, does not result in any additional aerodynamic resistance.

Abstract: A drainmast for discharging fluid from a body in motion, such as an aircraft in flight, may include a barrier disposed at a distal portion of the drainmast. The barrier may extend downstream from the drainmast trailing edge, and may be disposed at a negative angle of attack to a local free-stream airflow, thereby forming a downdraft over the barrier to prevent migration of discharged fluid towards an aircraft skin. In some embodiments, the drainmast may include one or more vanes, disposed internally within a discharge conduit of the drainmast, for deflecting fluid flow within the drainmast towards a direction of free-stream airflow outside the drainmast. Methods for channeling fluid away from an external surface of an aircraft in flight are also disclosed.

Abstract: Methods and systems for promoting precipitation from moisture-bearing atmospheric formations are described. A composition comprising a precipitation stimulating material and a volatile liquid agent is located on an aircraft and subject to one or more aircraft-generated pressures during aspersion. A first pressure is a pressure for expelling the composition from the aircraft. A second pressure results from combination between air and aircraft velocity. A third pressure is an ascending pressure resulting from expelling the composition from the aircraft at a lift portion location of the aircraft where only a lift force is applied to the aircraft during flight.

Abstract: A carriage and release system for stores (armaments such as rockets and bombs) on an aircraft includes a bracket adapted for attachment to the aircraft. A pylon is mounted on the bracket for movement in a pitch direction relative to the aircraft. A mechanism is provided to power the pitch movement and position it at a predetermined angle relative to the aircraft. A variety of stores carriers may be employed with the pylon. Subcarriages may also be mounted to the pylon for attaching additional stores carriers.

Abstract: The lighter-than-air vehicle for shading is an airborne, movable system that provides sun shade for an open area. The vehicle is a substantially flat flying device having upper and lower surfaces, and which is filled with a lighter-than-air gas or gases, such as helium or hydrogen. The vehicle may be tethered to the ground through control wires, or may be fully autonomous and controlled by propeller fans. The required power may be provided by wire from ground, or through a portable power source, such as solar cells, mounted atop of vehicle. The vehicle has sun sensors that allow it to track the sun, and provides around the clock shaded area underneath its surface. The vehicle can also have pressure sensors and altitude sensors that may trigger an alarm in case of an emergency descent to the ground.

Abstract: Nowadays in aircraft on-board inert gas generation systems (OBIGGS) are used to generate inert gases. Cooled bleed air of engines or auxiliary turbines is fed to said OBIGGS systems. According to an embodiment of the present invention, an air supply device for an OBIGGS system in an aircraft is proposed that comprises a bleed position (1,2). By way of the bleed position (1,2), air from an air conditioning unit (4,5) on board the aircraft can be bled and can be fed to the OBIGGS system. There is thus no need for an additional heat exchanger and an additional ram-air channel. Maintenance expenditure and air resistance are thus reduced.

Abstract: A lightning protection system, method and aircraft are provided for reducing the flammability of jet fuel spilled during an in-flight refueling operation between a supplying aircraft and a receiving aircraft. An inert gas is injected adjacent to a refueling interface in order to displace oxygen in the fuel-air mixture and thereby reduce the ability of the fuel vapor to ignite upon occurrence of an ignition source such as lightning. The refueling system may comprise a boom or a hose and drogue type device.

Abstract: Drain masts of commercial aircraft need to be heated in order to prevent freezing caused by the low outside temperatures when the aircraft travels at a corresponding altitude. An exemplary embodiment described in the application pertains to a drain system for an aircraft that can be used for draining liquids or gases from the aircraft or for drawing air into the aircraft. In this case, the liquids or gases are heated by means of a coolant that receives its thermal energy from a thermal or electrochemical process being carried out on board the aircraft. Consequently, the waste heat produced by the thermal or electrochemical process being carried out on board the aircraft, for example, a fuel cell process, can be carried off outboard via the drain system. In addition, the coolant can be advantageously utilized for cooling the thermal or electrochemical process.

Abstract: A method and apparatus for aerial fire suppression utilizing a potable fire retardant chemical dispensing system, readily adaptable, without extensive aircraft modification, to various makes of aircraft, for dispensing current types of forest and range fire fighting chemicals. The aerial delivery system is self contained and reusable. It enables cargo/utility aircraft to carry and dump a load, under control. The aerial delivery system is capable of attachment at the wing box, pressurized delivery from the nozzles, and nozzles directed straight downward.

Abstract: Apparatus for aerial refuelling comprises a frame 2 for attaching around an aperture in an aircraft floor 3, and a movable hose drum housing 4 pivotally mounted on the frame. The hose drum 12 may be stowed within the aircraft, and moved into the aperture, for example using screw jacks 20, for deployment of the drogue 40. Since the hose is deployed from a position nearer the outside of the aircraft, the hose does not scrape the edge of the aperture even when lying at a shallow angle to the aircraft.

Abstract: An enhanced aerial delivery system addresses issues raised when large quantities of fluids, powders, and other agent materials are to be transported in and aerially dispersed by aircraft. Some aspects include positioning and securing of tanks aboard the aircraft to facilitate management and safety of the tanks and aircraft. Other aspects address coupling of the tanks and associated piping to lessen structural effects upon the aircraft. Further aspects deal with channeling, containing, and dumping stray agent materials that have escaped from the agent tanks on board the aircraft.

Abstract: A positioning system, device, and method are provided to facilitate the in-flight positioning of two aircraft relative to one another such that a second aircraft is guided to an in-flight refueling position relative to a first aircraft. The system, device, and method of the present invention provide a signal emitted from a positioning device carried by the first aircraft, wherein the signal defines a signal envelope containing the in-flight refueling position. The signal is adapted to be receivable by the second aircraft such that the signal may guide the second aircraft to the in-flight refueling position relative to the first aircraft.

Abstract: A method and apparatus for aerial fire suppression utilizing a potable fire retardant chemical dispensing system, readily adaptable, without extensive aircraft modification, to various makes of aircraft, for dispensing current types of forest and range fire fighting chemicals. The aerial delivery system is self contained and reusable. It enables cargo/utility aircraft to carry and dump a load, under control. The aerial delivery system is capable of attachment at the wing box, pressurized delivery from the nozzles, and nozzles directed straight downward.

Abstract: A spray washer structure used for attaching to an aircraft and washing insulators on high-voltage transmission lines includes a pivot seat, a core tube, an inner tube, and a nozzle. The pivot seat is supported by a plurality of legs and a rear leg that are attached at the aircraft. The mid-section of the core tube is pivotally connected to the pivot seat by the use of a pivot, and an end portion of the core tube is connected to at least an inclined resilient buffer link at another end portion of the pivot. The innertube is passed through and pivoting within the core tube. The nozzle is secured at the front end of the inner tube by an adjustable joint. Moreover, the nozzle is also connected to a hose connected to a water source.

Abstract: The present invention blocks and/or attenuates the upstream travel of acoustic disturbances or sound waves from a flight vehicle or components of a flight vehicle traveling at subsonic speed using a local injection of a high molecular weight gas. Additional benefit may also be obtained by lowering the temperature of the gas. Preferably, the invention has a means of distributing the high molecular weight gas from the nose, wing, component, or other structure of the flight vehicle into the upstream or surrounding air flow. Two techniques for distribution are direct gas injection and sublimation of the high molecular weight solid material from the vehicle surface. The high molecular weight and low temperature of the gas significantly decreases the local speed of sound such that a localized region of supersonic flow and possibly shock waves are formed, preventing the upstream travel of sound waves from the flight vehicle.

Abstract: A fuel jettison system which provides pilot-initiated automatic operation to jettison fuel down to a 60 minute useable fuel remaining level while the manual operation, requiring the pilot to hold down the jettison panel switch, jettisons fuel down to a 20-minute useable fuel remaining level. The pilot can interrupt jettisoning at any time. This termination sequence operates in either automatic or manual mode. The port and starboard main fuel tanks jettison fuel independently through independent shutoff valves and associated circuit logic to thereby maintain aircraft balance.

Abstract: The Variable-Force Payload Ejecting System, residing within an air vehicle, utilizes multiple pressure generators, one or more of which may be activated, to produce variable levels of force. A controlling computer within the air vehicle determines when and how much pressure needs to be generated to eject a given item, such as a submunition, from the vehicle. In its determination, the computer factors in the vehicle's forward velocity and height over the intended target at the time of ejection and the characteristics of the particular submunition to be ejected. An activating mechanism activates one or more pressure generators to produce the determined amount of pressure. The pressure thusly generated acts on an inflatable tube that inflates and expels the selected submunition. The result is a more precise delivery of the submunitions onto the intended targets.

Abstract: An aircraft spraying conversion kit which provides for the aerial dispensing of a fire extinguishing agent. The kit includes a dispensing manifold assembly removably coupled to an open aircraft door which is supported by a support frame having two parallel support legs which also lock the opened aircraft door in a predetermined open position while the aircraft is in flight.

Abstract: Aerial dispersion systems that may be employed to allow rapid and temporary conversion of aircraft for aerial dispersion purposes, such as aerial fire-fighting. The aerial dispersion systems may be implemented using modular components that may be configured for compatibility with conventional cargo loading and unloading systems of modern aircraft, including side-loading cargo systems of wide body passenger and cargo aircraft having high lift capacities. The aerial dispersion systems may be rapidly installed in a large fleet of high capacity aircraft in response to a wildfire or other rapidly-developing emergency such as an oil spill, chemical or biological contamination incident, building or refinery fire, etc. After use, the aircraft of the fleet may be rapidly de-modified and returned to original condition.

Abstract: An in-flight refueling system and method are provided to extend and retract an in-flight refueling device between a stowed position and an extended position relative to a tanker aircraft. The system and method of the present invention provide an induction device configured to extend and retract the in-flight refueling device such that the in-flight refueling system requires less maintenance and may be packaged in a compact, low-profile arrangement so that the in-flight refueling system may be carried by a variety of tanker aircraft in a variety of different configurations.

Abstract: A chemical distribution control and guidance system operates for controlling the distribution of airborne product via an aircraft passing over a target. A weather station is positioned at various altitudes for use in determining an appropriate aircraft altitude for distributing the chemical to the target. A second weather station positioned near the target transmits weather data in real time to a central communications station and the aircraft for providing guidance in accurately, safely and effectively distributing chemicals onto the target.

Abstract: An atomization chamber apparatus used for aircraft pesticide delivery, which has an open ended walled chamber, divided into left and right sections, each having outer and inner segments, each segment having a top and a bottom wall, the outer segments having a same radius concave upper wall and a convex lower wall, while the inner segments have a same radius convex radius upper wall and a concave lower wall. A nozzle injector connectable to a fluid pesticide source is laterally disposed in an inner segment. The nozzle is chosen such that exiting pesticide will not impact the chamber walls, and the radii of the segments are chosen such that the speed of pesticide atomization by the incoming air is slowed down to reduce fines upon pesticide impact, and the speed of the pesticide air mixture on exiting the chamber is increased to substantially match the airspeed of the aircraft.

Abstract: A drain, for example for an aircraft engine support strut, arranged on the trailing edge of the rear secondary structure of the strut. The drain includes a conduit with a substantially horizontal axis and a substantially rectangular cross-section, taken in a plane parallel to the trailing edge, the conduit closed at an outer extremity by a terminal portion with a substantially ogival cross-section taken in the axis of the conduit and including at least one opening for drainage with an elongated shape on at least one of the opposing lateral walls.

Abstract: Excessive fuel is dumped by ejection under a pressurized outflow velocity from an aircraft during flight as jets in a direction parallel to air stream flow relative to the aircraft, from a rearwardly facing exit opening of a fuel jettison device mounted on the lower surface of the aircraft, with the exit fixedly spaced below the lower aircraft surface a short distance to avoid the Coanda effect while reducing or eliminating fuel and fuel mist impingement on aircraft surfaces.

Abstract: A firefighting bomblet includes a container having rigid supportive walls that together define a faceted-sphere shape, a cavity disposed inside the container and defined by the walls, and an opening in one of the walls for filling the cavity with a fire retardant. The bomblet can further include a weak seam formed in one of the walls, the weak seam being adapted to be more easily ruptured than the remainder of the walls. A method for aerial firefighting includes the step of dropping at least one of the containers enclosing a fire retardant from an aircraft over a fire.

Abstract: An aircraft attached apparatus/method for spraying pesticides having two propeller shafts attached to the aircraft. Each shaft has a full feathering propeller mounted at the forward ends of the propeller shaft and a control cable extending to the cockpit. High pressure pumps, typically piston pumps, are mounted on the aft ends of each of the propeller shafts. The input side of the pumps are connected to a tank, and the output side is connected to respective matrix spray boom assemblies. The forward ends of each of the spray boom assemblies are connected to the output side of each respective pump. Spray nozzles, typically impingement nozzles, are attached to each of the aft ends of each spray boom. The high pressure pumps have an electrically operated magnetic brake attached thereto, and each of the spray boom assemblies have a pressure transmitter connected to a digital display in said aircraft.

Abstract: Methods and apparatus for illumination of aerial refueling hoses are disclosed. In one embodiment, a conduit for transferring a flowable material includes a wall member. A plurality of reflective members are at least one of formed within an outer layer of the wall member and disposed on an outer surface of the wall member. The reflective members are adapted to at least partially reflect light incident thereon. In one aspect, the reflective members include reflective glass beads. In a further aspect, a first portion of the wall member has a first concentration of reflective members, and a second portion has a second concentration of reflective members.

Abstract: An in-flight refueling system, alignment system, and method are provided for substantially automating the positioning and engagement of an in-flight refueling system carried by a first aircraft with respect to a refueling receptacle carried by a second aircraft so as to facilitate an in-flight refueling operation between the first and the second aircraft. More specifically, the present invention provides for the alignment of the in-flight refueling boom with the refueling receptacle such that an extendable nozzle may extend from the in-flight refueling boom and engage the refueling receptacle to initiate an in-flight refueling operation.

Abstract: An apparatus is for use with a container of liquid that is suspended from an aircraft flying over a ground target area. The container has an outlet through which the liquid is dropped from the container. The apparatus includes a diffuser configured to diffuse the liquid exiting the container outlet horizontally outward beyond the container into the air above the ground target area, whereby the liquid is diffused over a correspondingly wide area. The liquid can be fire extinguishing liquid, and the ground target area can be a forest fire.

Abstract: A combination of an aircraft and spraying apparatus for spraying suspensions or solutions having predetermined characteristics independent of the speed of the aircraft, the apparatus consisting of a mounting frame attached to the underside of the aircraft, a plurality of bearing braces attached to the frame and a propeller shaft mounted through the bearing braces. A full feathering propeller is mounted on the forward end with a control running to the cockpit of the aircraft, and a rotary piston type high pressure pump connected to the aft end of the propeller. The input of the pump is connected to a supply tank in the aircraft and the output is connected to a spray boom. The spray nozzles consist of high pressure impingement nozzles.

Abstract: A pump system for loading fluid into a tank onboard a translating aircraft includes a substantially rigid tube member having a diving device on the distal end of the tube member. A strut structure may also be provided on a front face of the tube member. In use, the tube member is directed rearward relative to the translating aircraft so that splashing of fluid onto the underside of the aircraft is substantially avoided.

Abstract: An aircraft refueling boom load alleviation system uses received light to detect boom displacement and generates a control signal to correct the displacement. Both a set of flight surfaces and a plurality of light imageable targeting sights are disposed on a refueling tube. At least one digital camera converts the light imageable shape of each of the targeting sights to individual pixel images. The pixel images converted by the digital camera are input to a computer system. The computer system recognizes either a displacement of pixel images or a quantity change of pixels between pixel images as a displacement of the refueling tube. The computer system calculates the displacement of any of the pixel images. A signal is generated to control the refueling tube flight surfaces to correct the displacement.

Abstract: A chemical distribution such as a mosquito control guidance system is operable for controlling the distribution of airborne product via an aircraft passing over a target field. The system includes a weather station carried by a helium balloon positioned at aircraft altitude which communicates with a ground weather station positioned at or near the target field for transmitting weather data in real time to a central communications station and the aircraft for providing guidance in accurately, safely and effectively distributing chemicals onto the target field.

Abstract: A lighter-than-air airship system, having a multitude of uses, with a primary purpose being the dispensing of water over a raging fire, where access by personnel and ground equipment is difficult. The airship system comprises an aerodynamically configured structure having a semi-rigid keel or skeleton, where lift is provided in part by helium, with the keel mounting a liquid management mechanism preferably consisting of a reservoir open to the outside for resupply of liquid or water, a conduit leading to a holding tank, and a piping distribution and nozzle assembly below the airship system to spray or dispense the liquid or water, like an artificial rain, over selected areas to control or extinguish the raging fire. Alternate systems are provided for replenishing or filling the holding tank from ground locations.

Abstract: An unmanned, real-time, printed material generation and dispersal system includes a standardized shipping container houses at least one printing module capable of generating printed materials, a controller module for controlling the generation of the printed materials and monitoring status of the printing module, a communications module for communicating with the printing module and transmitting the status to a remote location, and a dispenser for receiving the printed materials so-generated and expelling them from the shipping container.

Abstract: A method for protecting an aircraft against a threat that utilizes an infrared sensor includes providing a plurality of dispensable infrared sources transported in an infrared-source dispenser with the aircraft. A set of infrared-emitting properties of the infrared sources is selected responsive to a set of infrared detecting characteristics of the infrared sensor. A modulated pattern of the infrared sources is dispensed from the infrared-source dispenser responsive to at least one of the set of infrared detecting characteristics of the infrared sensor, and a geometric engagement scenario of the aircraft and the threat.

Abstract: An aircraft refueling boom load alleviation system uses received light to detect boom displacement and generates a control signal to correct the displacement. Both a set of flight surfaces and a plurality of light imageable targeting sights are disposed on a refueling tube. At least one digital camera converts the light imageable shape of each of the targeting sights to individual pixel images. The pixel images converted by the digital camera are input to a computer system. The computer system recognizes either a displacement of pixel images or a quantity change of pixels between pixel images as a displacement of the refueling tube. The computer system calculates the displacement of any of the pixel images. A signal is generated to control the refueling tube flight surfaces to correct the displacement.

Abstract: A pump system for loading fluid into a tank onboard a translating aircraft includes a substantially rigid tube member having a diving device on the distal end of the tube member. A strut structure may also be provided on a front face of the tube member. In use, the tube member is directed rearward relative to the translating aircraft so that splashing of fluid onto the underside of the aircraft is substantially avoided.

Abstract: A system for dispensing a liquid from an aircraft to extinguish a fire has a container located in a body of the aircraft for storing the liquid to extinguish the fire. A boom is coupled to an exterior section of the body of the aircraft and to the container. The boom has a hollow interior section and a plurality of openings formed on a bottom section of the boom. The openings are used for dispensing the liquid from the container. A pump is coupled to the container and the boom for dispensing the liquid from the container and out through the boom. A rotating mechanism is coupled to the boom for rotating the boom.