Abstract: The present invention is a de-icing system that uses electro-magnetic actuators mounted within the airfoil of an aircraft to effect de-icing. Advantageously, the actuators have low-energy requirements. Each actuator includes conductive strips fabricated on a flexible dielectric sheet. The conductive strips are wound into coils with the actuators shaped into a flattened elongated tube. The axis of the winding coils is coincident with the longitudinal axis of the elongated tube. Low adhesive coatings may be used to enhance the efficiency of the electro-magnetic coils in expulsing the ice accretion.

Abstract: A device for treating the exterior of an aircraft, more particularly the wing and tail surfaces of an aircraft, comprising two gantries disposed on either side of a parking guide line on an aircraft parking place. The gantries are placed to be moved towards one another in a direction transversely to said parking guide line, from a position in which the gantries are mutually spread corresponding to the wing span of an aircraft. Said gantries are each provided with an elongate support beam that extends substantially parallel to said parking guide line and is provided with means for dispensing a treatment fluid, which means is formed by at least one spraying tube extending longitudinally of the respective beam, said spraying tube is equipped with longitudinally spaced spraying nozzles that cooperate with independently controllable valves.

Abstract: This invention overcomes the disadvantage of the prior systems and produces a high velocity specially formed and constituted pressure aerodynamic stream system for efficiently and effectively removing ice from an aircraft. The specially formed stream system includes a stream within a stream, wherein a deicing fluid such a glycol is entrained within and encased by a surrounding jacket of entraining fluid such as air. This deicing is now known as coaxial stream/stream within a stream deicing. The special nozzle allows the stream to maintain fluid separation over its flight path so that aircraft contact is made by to be known as coaxial stream/stream within a stream deicing. The coaxial stream/stream within a stream deicing is further enhanced by pressurizing the stream to deliver the stream as a high pressure, high velocity stream to improve the aerodynamic sweeping action of the airstream.

Abstract: An apparatus for deicing aircraft includes a vehicle frame, such as part of a truck, and a boom having one end mounted on the vehicle frame and a free end. A compressor unit is mounted on the boom and includes a hydraulic motor having an output and a centrifugal compressor operatively connected to the hydraulic motor output. A deicer air jet nozzle is connected at the free end of the boom and operatively coupled to the air outlet of the centrifugal compressor for receiving air and discharging the air for a deicer application.

Abstract: An apparatus for deicing aircraft includes a vehicle frame, such as part of a truck, and a boom having one end mounted on the vehicle frame and a free end. A compressor unit is supported by the boom and includes a motor having an output and a centrifugal compressor operatively connected to the motor output. A deicer air jet nozzle is located at the boom and operatively coupled to the air outlet of the centrifugal compressor for receiving air and discharging the air for a deicer application.

Abstract: A nacelle having a porous structure is provided with laminar flow control and contamination protection. In region B suction through a composite layer is achieved by evacuating a chamber adjacent the inner surface of the nacelle to provide laminar flow control. At the leading edge of the nacelle a sintered metal sheet is attached to an inner surface of the composite layer to control the flow of a liquid over the leading edge of the nacelle. The liquid is contained in a chamber adjacent the sintered metal sheet which is defined by a backing sheet which has a series of depressions therein. Hot air fed through a perforated pipe impinges upon the backing sheet and the depressions transmit heat to the sintered metal sheet. The sintered metal sheet has good thermal conductivity and in turn heats the porous composite layer to prevent the formation of ice thereon.

Abstract: A system for collecting and recovering de-icing fluid that is sprayed onto an aircraft. The de-icing system includes a mat that is assembled onto the approaching ramp of a runway. The de-icing mat has a plurality of channels that collect and direct the de-icing fluid to the outer edges of the mat. The de-icing fluid is removed from the mat by a vacuum system. Coupled to the vacuum system is a filter system that separates the de-icing fluid from other fluids such as oil, water, etc., so that the de-icing fluid can be used again. The mat has a plurality of heating elements that prevent the de-icing fluid from freezing on the mat and provide heat to the underside of the aircraft.

Abstract: A deicer includes a water tank storing water and an antifreeze solution tank storing an antifreeze solution. The water tank and the antifreeze solution tank are provided with heat exchangers, respectively. Pumps are further provided for feeding the water and the antifreeze solution in the respective tanks to a spray nozzle for spraying out a mixture of the water and the antifreeze solution. A gas turbine is provided for driving the foregoing pumps. Exhaust gas of the gas turbine is introduced into the heat exchangers through a control of valve switching so as to hold temperatures of the water and the antifreeze solution in the respective tanks to be constant. Further, bleed air of the gas turbine is fed to an air nozzle so as to be jetted out therefrom.

Abstract: A system for the forced air de-icing of aircraft is described which includes a source of pressurized air and an axisymmetric, high momentum focused air jet nozzle having an inlet of diameter D and an outlet of diameter d with an axisymmetric contour therebetween defined by a converging portion of first radius near the inlet and a reflex portion of second radius near the outlet, the converging and reflex portions being connected by a convergent conical portion tangent to both the converging and reflex portions and having an angle of convergence equal to or less than 30.degree., wherein D is equal to or greater than 2d, the first radius is equal to or greater than D, the second radius is equal to or greater than d, and the length of the nozzle is equal to or greater than 1.5 D, and an insulated conduit for conducting pressurized air from the source to the nozzle.

Abstract: An aircraft maintenance robot (20) for maintaining aircraft surfaces is described, that includes a maintenance tool (228), for example a nozzle (78), conduits and a pump, which supply fluid to the maintenance tool, which sprays the fluid on aircraft surfaces; movable arm with rotatable hinges and wrists such that a manifold to which the maintenance tools are coupled may be positioned in response to control signals; and a processor which, after accounting for the position of the aircraft, the weather conditions, and the physical dimensions of the aircraft, generates the control signals used to position the maintenance tool such that, after positioning the aircraft, the maintenance operation may be performed without human intervention. The preferred embodiment of the present invention discloses the use of the maintenance robot (20) for deicing aircraft. A wide variety of interchangeable end effectors, however, may be used for a wide variety of applications.

Abstract: A fluid recapture system collects residual waste fluids generated during airplane washing or de-icing procedures and separates and recycles these fluids to prevent contamination of storm water drainage and sewer systems and ground water supplies. The fluid recapture system includes a containment mat, a triangular berm with a resilient foam center surrounding the containment mat, a vacuum system located on the containment mat and recycling apparatus connected to the vacuum system. The recycling apparatus includes a pump for withdrawing fluid from the containment mat through the vacuum system and into the recycling apparatus. The pump withdraws the water from the containment mat and sends it to an effluent storage tank. From the effluent storage tank, the water is cycled through a hydro cycle machine, a reverse osmosis tank and finally into a clean water storage tank. The clean water can be reused in the airplane washing procedure.

Abstract: An apparatus is provided for chemically deicing aircraft on the taxiway. The apparatus includes a series of nozzles to dispense deicing solution onto the wings of an aircraft, and utilizes photoelectric sensors to detect when the nozzles are appropriately positioned to dispense the deicing solution, thereby conserving deicing solution. Recycling means are provided to collect, purify and concentrate used deicing solution for further use. The apparatus is further provided with extendable telescoping lift cylinders and rotating delivery arms from which the nozzles depend, thereby allowing the device to accommodate aircraft of different dimensions and design.

Abstract: An aircraft servicing system comprises four robot arms mounted to the ground so as to form a lane with the base of two of the robot arms delineating one side of the lane and the base of the other two robots delineating the other side of the lane. The robot arms may assume a low position which allows an aircraft's wings to pass over the arms while the aircraft enters the lane between the arms. Thereafter, the arms may be moved so that a nozzle array at the end of each arm may de-ice or wash the aircraft. Subsequently, the arms may again assume a low position to allow the aircraft to leave the lane. Each robot arm has an elongated member connected to the base by a yaw joint, a first arm segment connected to the elongated member by a pitch joint, second arm segment connected to the first arm segment by a pitch joint, and a third arm segment connected to the second arm segment by a telescoping joint.

Abstract: A system for de-icing aircraft in a de-icing area includes a first recessed storage area located substantially below ground level on a first side of the de-icing area. A first spraying boom, having at least one boom section, is used to apply de-icing solution to surfaces of aircraft. A first spray nozzle, for applying de-icing solution to surfaces of aircraft, is supported by the first spraying boom. The first spraying boom may be raised out of the first recessed storage area when an aircraft needs de-icing and lowered into the first recessed storage area for storage when aircraft de-icing is complete.

Abstract: An aircraft maintenance robot (20) for maintaining aircraft surfaces is described that includes a maintenance tool (228), for example a nozzle (78), conduits and a pump, which supply fluid to the maintenance tool, which sprays the fluid on aircraft surfaces; movable arm with rotatable hinges and wrists such that a manifold to which the maintenance tools are coupled may be positioned in response to control signals; and a processor which, after accounting for the position of the aircraft, the weather conditions, and the physical dimensions of the aircraft, generates the control signals used to position the maintenance tool such that, after positioning the aircraft, the maintenance operation may be performed without human intervention. The preferred embodiment of the present invention discloses the use of the maintenance robot (20) for deicing aircraft. A wide variety of interchangeable end effectors, however, may be used for a wide variety of applications.

Abstract: A storage tank is used to store a large quantity of pseudoplastic deicing fluid. The fluid is stored at an ambient storage temperature. The storage tank has an outlet which is preferably a valve located on the floor of the tank. A heater is provided to rapidly heat only a portion of the fluid in the tank to a required delivery temperature estimated at between 160 and 180 degrees Fahrenheit. Once a portion of the fluid is heated to the appropriate temperature, the valve is opened and the heated fluid is delivered out of the tank through the valve. Heat is transferred to the fluid in a heating area creating a predetermined dynamic temperature pattern within the fluid when the outlet is in the closed position and a predetermined steady state temperature pattern within the fluid when the outlet is in the open position.

Abstract: The use of potentially toxic deicing fluids can be substantially reduced, sometimes by as much as an order of magnitude, by selectively providing air entrained deicing fluid in a air jet or blast. The delivery parameters, e.g. the flow rate of deicing fluid and the entraining air are adjusted according to the specific snow or icing conditions on the aircraft surface on each application. A choice of deicing fluids are available, typically Type I and Type II deicing fluids. Deicing fluids may be heated or unheated as determined by the operator choice according to icing conditions. The type and amount of fluid is mixed within a mixing nozzle attached to a depending operator bucket connected to a boom on a mobile vehicle. The flow rate and pressure of heated or unheated pressurized air mixed with the deicing fluid is also adjusted according to icing conditions.

Abstract: A storage tank is used to store a large quantity of pseudoplastic fluid. The fluid is stored at an ambient storage temperature. The storage tank has an outlet which is preferably a valve located on the floor of the tank. A heater is provided to rapidly heat only a portion of the fluid in the tank to a required delivery temperature estimated at between 160 and 180 degrees Fahrenheit. Once a portion of the fluid is heated to the appropriate temperature, the valve is opened and the heated fluid is delivered out of the tank through the valve. Heat is transferred to the fluid in a heating area creating a predetermined dynamic temperature pattern within the fluid when the outlet is in the closed position and a predetermined steady state temperature pattern within the fluid when the outlet is in the open position.

Abstract: The invention is a system for heating aircraft deicing fluid. The system is an aircraft deicer such as shown in FIG. 2 which includes an engine 210. The deicer systems comprises a tank 270 for holding deicing fluid. First pump means 250,252 and 254 are driven by engine 210 and pump deicing fluid from tank 270 through piping or conduit 266,264,230. Backpressure valve means 251,253,255 is positioned the outlet of the first pump means 250,252,254 respectively, to continuously, substantially and directly heat deicing fluid to a temperature sufficient to deice the aircraft.The system further comprises second pump means 212, 232 for directing deicing fluid through engine 210 to pick up heat rejected by engine 210. Once the deicing fluid has been pumped through engine 210, piping or a conduit means 216,222,228,230,266,264 connects the output of the second pump means 212,232 to the inlet of the first pump means 250,252 and 254.

Abstract: System for applying compounds protective against ice formation on airplanes and for also cleaning and washing at respective first and second locations of at least one unitary covered structure. The unitary covered structure can be at least seasonally, or more often as requirements dictate, shuttled between a location immediately adjacent the clear zone of a runway for cold weather, or storm, operations and a location remote from said clear zone for washing in warm weather operations. Both positions of the covered structure have dedicated supply and drainage system for the fluids supplied at each position. Several unitary covered structures of various dimensions at several locations adjacent to the clear zone of a runway are also shown.

Abstract: An anti-icing system for leading edges of an aircraft. Hot compressed air is discharged from a cavity behind the leading edge, through a multitude of small holes in the leading edge skin into the airflow impinging on the leading edge. In a first embodiment the anti-icing system utilizes part of the air distribution system in existence for a laminar flow control system. Instead of sucking air into the wing, as is done in the laminar flow control mode, the flow is reversed in the anti-icing mode, blowing hot compressed air out of the wing. In a second embodiment the anti-icing system is used solely in the anti-icing mode.

Abstract: An apparatus for both de-icing and anti-icing an aircraft in one "pass". A pair of units are positioned above and below the aircraft. Each unit has respective nozzles oriented in one direction for dispensing de-icing fluid/air onto the aircraft as it approaches the units. Each unit further has respective nozzles oriented in an opposite direction for dispensing anti-icing fluid/air onto the aircraft as the aircraft moves away from the units. The apparatus is bi-directional so that the aircraft may approach the apparatus from either of two opposite directions. Means are provided for collecting and recycling the run-off of the de-icing and anti-icing fluids, respectively.

Abstract: An apparatus and method for applying a heated mixture of propylene glycol based aircraft deicing fluid and water to an aircraft. Propylene glycol based aircraft deicing fluid is heated by means of a directly fired combustion heater. The heated aircraft deicing fluid is mixed with hot water to form a deicing mixture for deicing aircraft. Diaphragm type positive displacement pumps, having controllable volumetric outputs, combine the heated aircraft deicing fluid and the heated water in a desired ratio. The volumetric outputs of the pumps can be varied to achieve a desired proportion of aircraft deicing fluid to water.

Abstract: An improved apparatus for deicing an aircraft is provided and consists of a recycling system which applies deicing liquid onto an aircraft and then recovers the deicing liquid back so that the deicing liquid can be used again.

Abstract: A deicing system for applying a deicing mixture to an aircraft is provided. Water is enclosed in a first tank, and deicing fluid in a second tank. A first pump transfers water through a heater, to a heat exchanger located in the second tank. The deicing fluid is thereby heated to a desired operating temperature by the hot water flowing through the heat exchanger, with the flow of hot water controlled by a heater control device. The first pump and second pump transfer heated water and heated deicing fluid, respectively, to a mixing chamber. A mixing control means controls the respective flows to provide the desired mixture. The mixture of water and deicing fluid is then applied to the aircraft via a nozzle.

Abstract: The invention comtemplates preparation of glycol/water de-icing mixtures in a demand-operated system wherein index of refraction and temperature are continuously monitored in a recirculating loop. The supply of heat and changes in mixing proportions of separate flows of water and of glycol are monitored until such time as predetermined values of mixed-fluid temperture and refractive index are achieved. A computer accepts monitoring-signal values for mixed-fluid temperature and refractive index, and further accepts ambient-condition signal values for set-point variation in mixing proportions, as necessary for economical use of glycol in the mixture, under each of a plurality of different ambient conditions.

Abstract: An electrically conductive structural composite which can be heated by application of an electrical current. The structural composite includes a plurality of layers of structural fabric which have been treated and prepreged with a laminating resin and cured into a laminate structure. At least one of the layers of fabric is rendered conductive by being treated with conductive polymer produced by the steps of contacting an electrically insulating porous structural fabric with a liquid pyrrole; contacting the electrically insulating porous structural fabric with a solution of a strong oxidant capable of oxidizing pyrrole to a pyrrole polymer; and, oxidizing the pyrrole by the strong oxidant in the presence of a substantially non-nucleophilic anion and precipitating a conductive pyrrole polymer in the pores of the structural fabric. Electrical conducting means in electrical contact with the conductive layer are utilized for providing passage of electrical current for joule heating of the structural composite.

Abstract: A tank for heating deicing fluid in a mobile aircraft deicer comprises a submerged heat exchanger coil through which heating fluid passes. Propellers near the heat exchanger circulate the bulk of deicing fluid while it is being heated to help distribute the heat. Pivoting shutters isolate an area beneath the heat exchanger from the bulk of deicer fluid and from which deicing fluid is withdrawn by a pump. This allows the bulk of deicer fluid to be further heated in a "last-pass" before being discharged upon the aircraft. A method of heating deicing fluid using this apparatus is also disclosed.

Abstract: A mixing apparatus and system is described for controlling the mixture of a de-icing fluid and water. Water, supplied by a centrifugal pump, is monitored by a flow meter which sends a flow rate signal to a controller. Glycol is supplied by another centrifugal pump to a calibrated multi-port digitally controlled flow valve. The temperature of the glycol and the pressure differential across the flow control valve are monitored by sensors, and the controller controls the flow of glycol from the flow control valve to maintain the preset glycol concentration.

Abstract: A mobile aircraft deicer having a base unit, a boom connected to the base unit, a deicer nozzle connected to the free end of the boom, and a television camera connected to the deicer nozzle.

Abstract: The invention relates to an aircraft de-icing system comprising an aircraft-washing hardstanding (1) onto which an aircraft can be moved, and pipes and nozzles, (3) for spraying de-icing fluid onto the aircraft, and discharge and drainage pipes combined with a sloped impervious layer (11) for collecting and carrying away the fluid.In order to enable the fluid to be removed from the hardstanding quickly and reliably, the hardstanding is constructed so as to comprise a substantially planar surface layer (12) of so-called drainage asphalt, and an impervious layer (11) which is located beneath the planar surface layer and which slopes steeply down towards drainage pipes (15), so as to collect and carry away the de-icing fluid passing down through the surface layer (12). The system also preferably includes a pump (7) arranged to draw air down through the surface layer so as to entrain therewith any water vapor formed and thus prevent the formation of vapor clouds liable to rise from the hardstanding (1).

Abstract: This invention relates to a porous panel for use principally, but not exclusively, for the distribution of a freezing point depressant liquid on an aircraft surface in order to provide protection against atmospheric icing. The panel comprises an outer porous sheet over the surface of which the fluid is to be distributed, a backing sheet of microporous material in contact with one side of the outer sheet, and a sheet of fluid impervious material which is spaced from the microporous sheet. The sheets may be secured to one another by adhesive bonding over a region located outwardly of the space. The outer sheet may be a porous material, a reinforced porous plastic material or a drilled sheet material.

Abstract: A centralized deicing system includes, in one embodiment, a large fixed location supply tank of deicing fluid which is heated and supplied to a plurality of terminal boxes located at several aircraft loading ramps. The system includes a recirculation loop for preheating the conduits for the deicing fluid by circulating heated deicer fluid through them before application to an aircraft. Each terminal box includes a coupler for receiving ends of a hose employed on a movable vehicle used for deicing an aircraft to also preheat the hose. In one embodiment of the invention, separate tanks of water and glycol are provided, and the terminal box includes a mixing valve which can be remotely controlled by an operator for blending the heated water and glycol in the desired proportion depending on weather conditions.

Abstract: The forwardly open intake end of a jet engine, powering an aircraft, is screened against birds and other airborne objects by a conical cage formed from an array of metal rods converging on the engine axis, the rods being held together at the vertex of the cone by a solid tip and in an intermediate plane as well as at the cone base by a pair of metal rings. In flight, they are free to vibrate so as to shake off adhering ice particles. De-icing can be further promoted by feeding back exhaust gases from the rear of the engine to the interior of the cage through an external pipe.

Abstract: A method for deicing an aircraft having ice formed on its outer skin comprises heating a water solution substantially free of glycol to a temperature from approximately 160.degree. to approximately 190.degree. F. The water is then sprayed in a stream onto the skin under atmospheric conditions whereby the heated water will loosen the ice and wash the ice from the skin. The excess water solutionwhich falls from the airplane is drained away. The heated water forms a film on the skin and warms the skin to prevent additional ice from forming thereon. Under certain atmospheric conditions, the heated water film will evaporate from the skin, thereby chilling the skin and drying it so as to minimize the sticking of blowing snow and ice on the skin. The method minimizes the amount of glycol required for anti-icing.