Abstract: Provided is an emergency warning device useful for quickly warning persons in danger of being struck by a disabled aircraft during an emergency landing procedure. The emergency warning device consists of a mounting assembly, a sound emitting device, a power supply, and a switch. The mounting assembly consists of a door pivotably mounted on the cowling of the aircraft, the door having an external surface substantially flush with the external surface of the aircraft such that the aerodynamic characteristics of the aircraft are not substantially altered when the door is in a closed position. The power source selectively provides power, independent from the aircraft power, to the sound emitting device. The switch connects the sound emitting device to the power source upon activation of the emergency warning device. The mounting assembly exposes the sound emitting device in an open position upon activation of the emergency warning device such that the sound emitting device is audible external to the aircraft.

Abstract: A whole-spacecraft passive isolation system consisting of a plurality of titanium flexures that act as soft springs to isolate a satellite from its launch vehicle is improved by the addition of piezoceramic wafers attached to the flexures. A low-pass filter feedforward controller is used to cancel out disturbances by applying out-of-phase signals to the piezoceramic wafers thereby creating a hybrid isolation system that significantly reduces the dynamic loads on the spacecraft.

Abstract: A portable, re-usable, battery-powered, electronic device for storing, displaying and modifying air traffic control information. The electronic flight data strip receives input data from an external data source via infrared or radio transmission, stores the data in an on-board memory device, displays selected portions of the received data for viewing by an air traffic controller, and receives and displays inputs from the air traffic controller either directly through integral switches or via aforesaid communications channels. All input and output data messages and air traffic controller commands may be stored and time tagged for later retrieval. The contents of the stored memory can also be interrogated and modified by external data processing devices. Following completion of the flight, the contents of the internal memory can be interrogated for the purpose of archiving or investigation and/or cleared for subsequent re-use on another flight.

Abstract: An advertising placard (20) having a substrate (30) and coloration material (34) is utilized to provide an unobtrusive and nondistracting advertisement on internal viewing surfaces (22) in commercial aircraft passenger cabins (24). The substrate (30) is preferably thin and transparent, and the coloration material (34) preferably has substantially the same color hue as the viewing surface (22) to which it is applied. Further, the coloration material (34) preferably has a color lightness within approximately .DELTA.7 of the color lightness of the viewing surface (22).

Abstract: The system provides engine maintenance information automatically from fault code data received from an onboard engine performance monitoring computer. The maintenance information is provided by an HTML repair guide electronically called by the control system using the fault code as part of the page address in the HTML guide. The control system automatically ensures that all fault codes are responded to, i.e. that maintenance personnel carry out the appropriate maintenance actions in response to each and every fault code, with a view to improve quality assurance of maintenance. Maintenance actions of maintenance personnel are automatically for the purposes of validating and/or generating warranty claim applications. The system also has a warranty claim report generator for processing aircraft maintenance action log data.

Abstract: A system, method, and computer program product assist a technician in troubleshooting an aircraft auxiliary power unit (APU). A portable computer is couplable of download the fault data captured in a memory of the ECU. The fault data corresponds to one or more instances of APU failure. The computer is further programmed to compare the fault data to predetermined fault patterns stored in a database. Each record of the database has one of the fault patterns, a corresponding fault indication, and a corresponding service recommendation indication. The computer is further programmed so that when a record in which the fault pattern matches the fault data is found, the corresponding fault indication and service recommendation are retrieved from the database and provided to the technician via the computer's display or other suitable output mechanism.

Abstract: An emergency vision device for use in a smoke emergency to enable a user to look through a windshield or view an instrument, comprises a housing; an inflatable enclosure having a first end for being disposed toward a user, a second end for being disposed toward the windshield or the instrument, the inflatable enclosure being stored within the housing when not in use, the first and second ends having first and second transparent panels, respectively, such that visual information from beyond the windshield or from the instrument is transmitted through the second panel to the user through the first panel; a blower operably connected to the inflatable enclosure adapted to inflate the enclosure; a first switch for operating the blower; and a member operably connected to the inflatable enclosure and the first switch such that the switch is activated when the inflatable enclosure is removed from the housing.

Abstract: A control system for producing first and second fluid sources whose pressure difference is regulated to a desired value in response to four fluid supplies of independently variable pressures. The pressure of the first fluid source is not allowed to decrease substantially below the third fluid supply pressure or rise substantially higher than the desired value above the pressure of the third fluid supply. The pressure of the second fluid source is not allowed to rise substantially above the fourth fluid supply pressure or decrease substantially lower than the desired value below the pressure of the third fluid supply. The system may consist of a diaphragm-type pressure regulator which is responsive to the difference in pressure of the two fluid sources. One side of the regulator is selectively valved to connect to one of two pressure supplies while the other side is selectively valved to connect to one of two additional pressure supplies.

Abstract: The present invention provides a method of detecting an engine stall based on the intensity of ultraviolet light being sensed in the augmentor. The method is used to confirm a stall when the gas generator burner pressure sensor is operating properly, and as a back-up detection method when the burner pressure sensor fails, or when the burner pressure line to the control system ruptures and fails.

Abstract: A Satellite Weather Modification System (SWMS) uses earth satellites to harness solar energy to modify the thermodynamics and composition of the earth's atmosphere. SWMS has three subsystems: The first subsystem includes a network of earth satellites called Satellite Engines (SEs) used to reflect solar energy and/or transform solar energy into other forms of energy beams discharged at specified locations. The media at these locations and the media through which the energy beams pass absorb these energies and change them into heat. The second subsystem includes a large network of Remote Sensing Devices (RSDs). These sensors are used to measure local media compositions, dynamic parameters and thermodynamic properties. Sensor measurements are fed back to the third subsystem, which includes a network of Ground Control Stations (GCSs). GCSs provide energy beam guidance by estimating each beam's characteristics and its aim point trajectory as functions of time.

Abstract: The aircraft air conditioning energy recovery device exploits the high level energy in relation to the exterior, in the air conditioning air flow required for renewal, and involves the placement of the aircraft outflow valve in a duct through which all the air flows the duct being arranged from the pressurized cabin to the inside of the engine inlet diffuser, through the pylon and in some cases through the wing, with the air-conditioning flow being fed back to the input air flow through multiple openings on the inside wall of the inlet diffuser. The openings or grooves run at a slight angle to the direction of flow to avoid turbulence. The air conditioning input may be introduced through hollow radial guide vanes attached at the front end to the vanes of the first stage of the low-pressure compressor and to the hollow vanes, open at the back, in the first stage or stages of the low-pressure compressor stator where the pressure is lower than that of the cabin air.

Abstract: An ascent vent cover (24) for covering and sealing vent holes (22) in a payload launch vehicle (21) is disclosed. The ascent vent cover (24) includes a magnetic sheet (32) for covering the vent hole (22) and attaching the ascent vent cover to the payload launch vehicle, a plurality of magnets (34a, 34b, 34c, . . . ) for augmenting the holding strength of the magnetic sheet, and a stiffening panel (38) for facilitating the peeling of the ascent vent cover away from the payload launch vehicle (21). The magnets (34a, 34b, 34c, . . . ) are secured to the magnetic sheet (32) so that some are positioned in a circular pattern so as to surround the underlying vent hole (22) and others are positioned along a leading edge of the magnetic sheet (32). The stiffening panel (38) includes a cover portion (39) and a tab portion (40) for securing to the magnetic sheet (32). The magnets (34a, 34b, 34c, . . . ) are embedded in the cover and tab portions.

Abstract: An aircraft includes a system for managing check lists solely by operation of a four-position rocker switch having a center return position. The system includes check list data organized into three levels and automatically displayed upon occurrence of an abnormal condition.

Abstract: The system provides engine maintenance information automatically from fault code data received from an onboard engine performance monitoring computer. The maintenance information is provided by an HTML repair guide electronically called by the control system using the fault code as part of the page address in the HTML guide. The control system automatically ensures that all fault codes are responded to, i.e. that maintenance personnel carry out the appropriate maintenance actions in response to each and every fault code, with a view to improve quality assurance of maintenance. Maintenance actions of maintenance personnel are automatically recorded for the purposes of validating and/or generating warranty claim applications. The system also has a warranty claim report generator for processing aircraft maintenance action log data.

Abstract: A system and method is provided for rapidly reconfiguring a jet aircraft from a cargo or passenger configuration into a parabolic flight configuration. In the parabolic flight configuration, a zero-gravity condition is created in the aircraft cabin to simulate a weightless atmosphere which can be provided as entertainment to paying customers. Various aspects of the invention include a hydraulic system design change which prevents loss of hydraulic function during a zero-gravity condition and a strap-down accelerometer which provides a visual indication of the parabolic flight condition. Additional interior modifications include removable padding areas, a dual-purpose interior gill liner, modified oxygen systems, handrail attachment fixtures, modified emergency lighting systems, and a palletized floor assembly.

Abstract: A safety system for visual flight reference system for simulating the geography around an airplane during the landing and the take-off under zero visibility conditions. The inventive device includes a display screen, a keyboard, a hold-down bracket and a central processing unit.

Abstract: For humidifying the air in an aircraft cabin, individual spray nozzles are each directed towards a zone including the face of a passenger and fed with water via a controllable closure valve. Typically, each spray nozzle is fed by a respective cartridge or can of pressurized water located in a receptacle formed in a seatback.

Abstract: A pitot tube cover is arranged with a slot to encompass the pitot tube and a wind surface that is perpendicular to the direction of travel of the vehicle upon which the pitot tube is mounted. Once the vehicle reaches a predetermined speed, sufficient force is applied against the wind surface that causes the cover to rotate about a pivot area, freeing itself from the pitot tube and allowing the pitot tube to operate normally.

Abstract: An aircraft engine vibration analysis system is provided with at least one vibration sensor disposed proximate an aircraft engine. The analysis system is further provided with a vibration analysis module for receiving an input from the vibration sensor and generating an output representative of vibration characteristics of the aircraft engine. The analysis module is provided with a multiple pin input port which is connectable to the vibration sensor. The analysis module is further provided with test sequence select circuity which is in electrical communication with the input port for implementing an appropriate vibration analysis sequence in response to measured conductivity between pins of the multiple pin input port. The analysis system is further provided with a sensor connecting cable which is connectable to the vibration sensor and the analysis module input port.

Abstract: Security apparatus and a method for preventing theft or unauthorized removal of instruments from the cockpit instrument panel of an aircraft and for preventing theft or unauthorized use of the aircraft. The apparatus includes a rigid plate substantially covering the instrument panel and two rigid arms pivotally secured to the plate inwardly of the columns respectively and laterally pivotable rearwardly away from and forwardly toward the plate. Each of the arms include an end portion for restrainably engaging the aircraft flight control yokes against rotation when the arms are pivoted to extend rearwardly away from the plate while the columns are fully rearwardly extended and the yokes are fully rotated to one side. A locking device is engageable with the end portions of the arms for locking the arms rearwardly extended and for cooperating with the yokes to prevent forward displacement of the columns while securing the plate against the instrument panel.

Abstract: This invention discloses an apparatus for stabilizing a payload assembly including a payload, a maintaining apparatus for at least temporarily maintaining the payload in an airborne environment, and an elongate connection apparatus, which when extended has a vertical length greatly in excess of the combined vertical lengths of the payload and the maintaining apparatus, whereby angular stabilization is a function of the vertical length of the connection apparatus when extended.A method for stabilizing a payload assembly is also disclosed.

Abstract: An accessory mounting assembly for use in a helicopter, the assembly comprising a fitting for attachment to the helicopter in place of or in conjunction with a tail rotor pedal assembly on the flight deck of the helicopter, a post slidably engaged within a large bore in the fitting, and retained in position by a retaining pin. A platform on the second end of the post is used for supporting optional equipment and accessories. Alternatively, additional posts may be interchanged with the post for specialized applications.

Abstract: A cover and method for applying the cover unto the wing comprising a flexible material to cover the top surface of said wing, said material having a leading edge to cover the leading edge of said wing and a trailing edge to cover trailing edge of said wing; a first set of spaced apart attachment straps each said first attachment strap extending from said trailing edge of said cover under said wing for quick release attachment to said leading edge of said cover, so as to attach and quickly release said cover to said wing; a second set of spaced apart removal straps, each said straps extending from said leading edge of said cover over said wing for quick release attachment to said trailing edge of said cover so as to remove said cover from said leading edge to said trailing edge of said wing by pulling said removal straps.

Abstract: A system and method for creating visual images of aircraft wake vortices allows a user, such as an aircraft controller, to increase a number of airport transactions while maintaining a predetermined level of safety. Wake vortices are simulated in a three dimensional environment taking into account various aircraft, environmental, and atmospherical conditions. The simulated wake vortices are rendered from a perspective selectable by the user. The displayed image allows the user to direct aircraft around potentially harmful wake vortices.

Abstract: An arrangement of outlet devices for releasing into the atmosphere cryogenic, combustible exhaust vapors in the near-surface, flow-swept, outer area of aircraft, land vehicles and watercraft. The arrangement provides at least one outlet device on the top side of a component at the top end of a pylon, which is favorable in terms of flow, in the free, undisturbed air flow. Each outlet device is arranged, designed and oriented such that the exhaust vapor is released in at least one directed jet oriented to the rear or to the rear and upward, with or without a lateral component, and is kept away from air inlets, hot exhaust gas jets and other sources of ignition, as well as from surfaces of components.

Abstract: A method for measuring growth and magnitude of structural damage in a structure such as an airframe, as reflected by growth of a crack therein, by securing to a structural portion thereof at least one ligament assembly whose properties replicate such damage. The ligament assembly has a metallic load test coupon having a loading response substantially identical to a loading response of the structural portion and an artificial flaw simulating a metallurgical crack. The crack has a growth rate magnitude substantially identical to a magnitude of structural damage of the structural portion as such damage occurs. A crack growth measurement gage is in alignment with the crack of the test coupon and in communication with a recorder unit to record crack growth, and crack growth is compared to correlated structural damage of the structural portion as associated with such growth.

Abstract: A ground floodlight for an aircraft having a fuselage including a forward cargo door includes a generally flat lens having a first region for directing light toward the front cargo door and a second region for directing light generally forward to illuminate ground in front of the aircraft. The lens is generally flat and smooth and is adapted for flush mounting in the fuselage. A corresponding method for improving ground floodlight illumination includes directing light generated from a lamp within the fuselage in an outward direction and then redirecting first and second portions of the light toward the front cargo door and the ground in front of the aircraft, respectively.

Abstract: A fairing for an aircraft is provided, having a roll axis with a turret coupled to the front end of the fairing for rotation about the roll axis. An opening is formed through the front end of the turret in which a tracking member is supported for rotation between forward and rearward positions about a pitch axis transverse to the roll axis. The tracking member has a cavity with a primary optical mirror at one end and a transparent shield at an opposite end with a primary optical axis extending between the mirror and shield. The shield is slanted to minimize wind turbulence when the tracking member is located in a rearward position.

Abstract: An aircraft display combines speed error tapes and multiple speed reference bugs to produce a display which reduces pilot workload. The length of the speed error tape is indicative of the difference between a current aircraft speed and a reference speed. Multiple reference bugs are adjacent to the error tape and are indicative of the difference between the current aircraft speed and other selected reference speeds. The reference bugs move along the error tape thereby communicating the status of the current aircraft speed relative to the multiple reference speeds. The display reduces the need for the pilot to scan and analyze numerous instruments for the same information.

Abstract: A diverterless engine inlet system that integrates a "bump" surface with a forward swept, aft-closing cowl to divert substantially all of the boundary layer air from the inlet. The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The cowl couples to the body of the aircraft to form the remaining surfaces of the inlet and closes against the body of the aircraft at the aft-most points of the inlet opening. The bump and the cowl work together to divert low energy boundary layer air from the inlet during aircraft operation, thus eliminating the requirement for a boundary layer diverter. The diverterless inlet provides a lower cost, reduced complexity air induction system that can be used on a supersonic aircraft engine.

Abstract: The invention provides an aero-optical turret assembly that provides high Strehl ratios throughout a wide range of azimuthal look angles. The turret assembly includes a duct extending from aft of the turret to a location aft of an aerodynamic bulge of the turret assembly. During flight, a low pressure zone is formed at the exit end of the duct, aft of the aerodynamic bulge. This low pressure zone causes suction of air from the inlet of the duct, and therefore away from the outer surfaces of the aero-optical turret. By judiciously selecting the shape of the aerodynamic bulge, and the size and location of the inlet end of the duct, substantially all turbulent air can be removed from around the adjacent outer surfaces of the aero-optical turret, thereby removing the source of interference with electromagnetic radiation passing through the window of the turret at azimuthal look angles greater than +60.degree..

Abstract: A fuel time indicator which is removably mountable about a fuel tank selector switch for monitoring and displaying tank usage times for each of a plurality of fuel tanks is disclosed. The fuel time indicator comprises a portable frame including a switch position sensor for monitoring a plurality of positions of the fuel selector switch and generating a corresponding switch position signal. A timer generates a timing signal indicative of elapsed time. A controller responsive to the position signal and the timing signal generates tank usage times for each of the fuel tanks by selectively aggregating elapsed times. Visual indications of the tank usage times are provided by a display.

Abstract: A video monitor is deployed from an aircraft overhead storage compartment via a monitor-drive shaft selectively connected to an electric motor and retracted back into the compartment by a spring connected to the shaft. The monitor has limited rotational movement in both directions relative to the shaft. A bump sensor detects when the monitor has moved from its deployed position relative to the shaft as a result of being struck by a passenger and trips a solenoid. The solenoid, in turn, disengages the monitor-drive shaft from the motor and allows the spring to return the monitor to its stores position.

Abstract: A visual indicator is provided for warning a pilot of an engine compartment fire and comprises a housing which is mounted on the cowling enclosing the engine compartment. In one form of the invention, a lens and mirror arrangement is provided for transmitting light through the housing so that the pilot will be warned of the existence of an engine compartment fire.

Abstract: A device for the sensor signature reduction of cargo to be dropped from the air comprises a covering that essentially completely surrounds the cargo, which is made of a flexible material having a surface that reflects the expected radar radiation, wherein it is provided with openings for the inlet of ram air.

Abstract: A thermal and shock resistant data recorder assembly as an outer container (1) containing an inner container (2) which in turn houses one or more data recorder elements (3). The elements (3) which have a thin conformal coating thereon are encapsulated in an innermost cavity (4) of the inner container (2) in an Ester wax material which absorbs heat when changing from a solid to a liquid. An outermost cavity (8) surrounds the innermost cavity (4) in the container (2) and in turn contains a first insulating material which gives off water vapor when heated to absorb heat. Surrounding the inner container (2) in the outer container (1) is a second insulating material. The Ester wax material is enabled to leak when liquid into the outer container and from thence, if necessary, to the exterior of the outer container. This permits pressure equalization. The first insulating material is provided with a fusible material plug which melts under heat and allows the vapor to escape to the exterior of the assembly.

Abstract: Process for piloting an aircraft in order to improve a microgravity state and the corresponding system.Instead of supplying the pilot with an information linked with the instantaneous position of the equipment in free floating form (M), he is supplied with an information relative to the anticipated position of said equipment.Application to microgravity studies.

Abstract: An emergency aircraft start apparatus and method utilizing a donor aircraft to provide pneumatic and/or electrical power to a disabled receiver aircraft which is unable to be started due to a failure in the receiver aircraft's starting system or to the unavailability of ground auxiliary equipment.

Abstract: The acceptability of the steering angle between the nose wheel of an aircraft and the longitudinal axis of the aircraft during transportation of the aircraft on the ground using a wheeled vehicle (with or without a tow bar) is provided. The wheeled vehicle has a source of collimated radiation (such as a laser beam emitting unit, or an LED or other light source with a lens and/or aperture system) which directs a beam on a surface of the aircraft having at least two significantly different collimated radiation reflecting areas (e.g. a light material arc bounded by dark material marks). In response to radiation from the collimated beam, or lack thereof, reflected from the surface of the aircraft back to a receiver on the wheeled vehicle, it can be determined if the nose wheel steering angle is within an acceptable range (typically no more than between about 60.degree.-80.degree., which would damage the nose wheel).

Abstract: The system includes a platform assembly which includes a plurality of helium airships for support of an emitting electrode to produce a large amount of electrical charges, in the form of electrons, into the surrounding atmosphere. The electrons may be generated by various means, including field induced emission and ultraviolet induced emission and ionization. Also provided are a large bank of solar cells to produce the necessary power for the assembly and a propulsion system, either a propeller system or an ion engine. A positive electrode may also be included which collects the undesirable atmospheric elements, such as chlorine atoms, to which negative charges have become attached. Alternatively, the platform could be arranged to include a negatively charged surface at which chlorofluorocarbons, for instance, can dissociate after they come in contact with negative charges. Such an ion-propelled platform in the high troposphere or stratosphere could also be used for regional and/or global telecommunications.

Abstract: There is described a vehicle door assembly with shear layer control for controlling the airflow in and around an aperture in the vehicle fuselage. The vehicle door assembly consists of an upper door and a lower door, both slidably mounted to the exterior surface of the vehicle fuselage. In addition, an inner door is slidably mounted beneath the upper door. Beneath the inner door is an aperture assembly having an aperture opening positionable to be substantially flush with the exterior surface of the vehicle fuselage. Also provided are means for positioning the aperture assembly in an upward and downward direction in relation to the vehicle fuselage.

Abstract: This invention provides a static vent unit e.g. for use on the side of an aircraft and which in operation is subjected to airflow from any direction within a wide airflow incidence range comprises a generally flat plate having an outer surface for fitment generally to flush to an outer surface of the aircraft, a vent port through the plate for connection during operation to a static vent line in the aircraft, and a bulge on the plate outer surface surrounding at least part of a circumference of the vent port and having in cross section a convex curved upper surface extending radially inwardly from an outer edge on the plate to an inner edger on the plate adjacent the circumference of the vent port and adapted during operation to promote attachment of an airflow from within at least part of the airflow incidence range to its surface and direct the airflow into the vicinity of the vent port to provide a compensating increase in ambient pressure at the vent port.

Abstract: A waste water drain apparatus (1) is to be attached to the fuselage belly (2) of an aircraft. The apparatus (1) essentially includes a drain pipe (3), an aerodynamically shaped fairing (7) enclosing the drain pipe (3), an attachment flange (6) for connecting the apparatus to the aircraft, at least one temperature sensor (9), and either at least one heating element (8) or hot air inlet (13) for heating the drain pipe (3). An inlet end (4) of the drain pipe (3) is to be connected to a waste water system of the aircraft. An outlet end (5) of the drain pipe (3) exits rearward at the trailing edge of the fairing so that the lengthwise axis of the drain pipe outlet is substantially parallel with the air flow during flight.

Abstract: An aircraft wing protective cover system which is secured on an aircraft wing to cover and protect the wing from snow and ice build-up during winter weather includes a cover sheet configured to overlie the upper surface of an aircraft wing and to extend around and under the forward edge of the wing. The system also includes a pocket formed at an outer end of the cover sheet which encloses a tip of the wing, and perimeter strips attached to and extending along the perimeter of the cover sheet and cross strips attached to the cover sheet and extending between the perimeter strips to reinforce the cover sheet.

Abstract: An air data sensor strut made of a single block of material has one side finished in a smooth contour, and has grooves in an opposite side of the strut for receiving pressure carrying conduits or other elongated members such as a heater. The heater and conduits are secured in place with a filling of potting material and the open sides of the grooves are finished after filling so that the desired contour is provided for the opposite side of the strut. The strut has a thin cross-section because of the elimination of hollow interior spaces formed by spaced walls.

Abstract: An aircraft stall warning system includes an angle of attack sensor which provides a signal to an angle of attack processor which provides an angle of attack signal to a display. An air pressure sensor provides an air turbulence intensity ratio signal to an aerodynamic performance processor which provides an aerodynamic performance signal to the display. The display therefore simultaneously displays both theoretical stall margin and actual stall margin to thereby provide a pilot with wing contamination information.

Abstract: An aircraft maintenance elevation system comprising a plurality of elevator platforms and a plurality of electro-mechanical drive assemblies which are coupled to and operable to selectively raise and lower respective ones of the elevator platforms. The elevation system further includes a control device which is electrically connected to the drive assemblies and is operational in a first mode wherein the elevator platforms may be raised and lowered independently of each other and a second mode wherein the elevator platforms may be simultaneously raised and lowered.

Abstract: A static vent unit particularly for use in the side of a helicopter fuselage includes a support plate having a vent port and a strake extending generally horizontally below the vent port with an upper surface facing the vent port and generally perpendicular to the support plate surface, and airflow deflection means located below the strake to deflect airflow away from the strake when the unit is operating in an airflow from below the strake.

Abstract: An active noise control subassembly for reducing noise caused by a source (such as an aircraft engine) independent of the subassembly. A noise radiating panel is bendably vibratable to generate a panel noise canceling at least a portion of the source noise. A piezoceramic actuator plate is connected to the panel. A front plate is spaced apart from the panel and the first plate, is positioned generally between the source noise and the panel, and has a sound exit port. A first pair of spaced-apart side walls each generally abut the panel and the front plate so as to generally enclose a front cavity to define a resonator.

Abstract: A Pitot static tube cover made out of a rigid material skeleton covered with a ceramic braid. A cross-bar with holes is provided so that the Pitot static tube cover may be mounted or dismounted by a pole from the ground.