119 results about "Airplane" patented technology

The invention provides a system and method for automatically detecting foreign object debris (FOD) on airfield runways, belonging to the technical field of automatic control of aviation. The system comprises a detector, an optical characteristic database, an FOD database, an object motion state analysis device, an object physical attribute analysis device, an estimation device of threat severity grade of the object towards the airplanes, an alarm device, a remote monitoring device and a workstation removing device. By the system and the method, all-day, all-weather and full-automatic detection, identification and alarm can be carried out on the FOD targets and the accuracy of automatic detection and alarm can be substantially improved.

A combined transponder and DME system for use in an aircraft. An L Band transmitter is shared between transponder and DME.

A method of forming an exterior surface protective structure (12) for an aircraft (10) includes providing a surfacer (26) having a carrier on a metal mesh material (24) and an isolator (22) with resin in the surfacer and the isolator filling holes in the metal mesh to form a surface that may be covered with finishes (28), such as spray applied surfacers, primer(s) and a paint to provide a more robust structure that resists corrosion and prevents substrate microcracking, while providing rain erosion resistance, environmental durability, structural performance, and lightning protection in a lighter weight and less costly material.

A weather radar signal path for an aircraft. The signal path has an antenna, a digital down-converter, a first transceiver, fiber optic cabling, a second transceiver and a processing unit. The antenna is adapted to, in a first mode, receive reflected radar signals from atmosphere ahead. The digital down-converter is adapted to convert the reflected radar signals received by the antenna into digital radar signals at a lower frequency. The first transceiver is adapted to, in the first mode, at least transmit the digital radar signals through said fiber optic cabling. The fiber optic cabling is adapted to, in the first mode, transfer the digital radar signals between the first and second transceivers. The second transceiver is adapted to, in the first mode, receive said digital radar signals from the fiber optic cabling. The processing unit is adapted to, in the first mode, process the digital radar signals to generate weather information based on predetermined algorithm.

An electric, inductively-energized, multi-bladed, controllable-pitch propeller hub is configured with an internal battery, electronic control unit and electric internal reversible hubmotor, when energized by a voltage inducted across an air gap into an annulus of receiver coils that is mounted onto said propeller hub and when said propeller hub is attached to and operated with complementary electrical, electronic and mechanical components that enable wireless command signals, together forming a novel and versatile device whose operation can provide near-instantaneous modulation of aircraft thrust, lift and drag by the action of said propeller hub to actuate precise and equal changes to the pitch of each propeller blade through a full range of useful pitch settings, both during rotation of said propeller hub and when said propeller hub is stationary, with an innovation including a coaxial driveshaft that facilitates the removal and installation of said propeller hub from a propmotor.

The invention provides a flame trap cartridge 154 for use in a flame arrestor 50, the flame trap cartridge comprising a casing 160, and a foam component 170 having two opposite ends and at least one side edge, wherein the foam component is at least partially encased around at least one side edge by the casing. The invention also provides a flame arrestor, a method of preventing flame propagation into a fuel tanks and a method of operating an aircraft.

The invention discloses a sensor for monitoring metal abrasive particles in oil liquid on line. The sensor is a mutual inductance sensor and comprises an exciting coil and an inducting coil, wherein an oil path through which the oil liquid can pass is arranged in the center of a framework made of a magnetic inert material; the exciting coil and the inducting coil are coaxially wound on the framework; the inducing coil is positioned between the exciting coil and the framework; the axial length of the inducting coil is 1/4-1/2 of that of the exciting coil; and the axial center points of the inducting coil and the exciting coil are superposed. The sensor realizes zero compensation and adjustment by adopting a parallel measurement structure and is simple in structure, high in sensitivity, high in linearity and high in interference resistance. The sensor applied to on-line monitoring for the metal abrasive particles in the oil liquid is convenient to operate, high in instantaneity, high in measurement precision and accurate and reliable in monitored result and can be widely applied to military and civil fields and used for monitoring the pollution degree and the abrasion to the oil liquid of lubricating systems of mechanical equipment such as various air planes, naval vessels and automobiles and monitoring and diagnosing faults of the lubricating systems of the mechanical equipment to avoid safety accidents.

An Auxiliary Power System includes an APU controller and an aircraft load controller which include an APU load capacity algorithm which provides an uncomplicated and robust method of APU load control. The APU load capacity algorithm defines three load zones: a continuous APU load capacity zone (zone A); a time controlled zone (zone B); and a fault zone (zone C). Each zone is related to altitude to the service ceiling of the APU to provides consistent APU load capacity that addresses APU performance variation and deterioration effects to an end of the APU useful life.

Noise reduction conduit for non rotary components of aircraft engines, subjected to a characteristic range of temperatures of a gas turbine engine, constituted by an annular structure composed of an aerodynamic wet wall (10a, 10b), perforated and resistant mechanically and thermally; of a dry wall (12a, 12b), not resistant and of light weight; and of some intermediate elements to which both walls are mechanically attached and that define a jump or difference of temperature between the wet and dry walls; between which wet (10a, 10b) and dry walls (12a, 12b) there are partitions that define cavities (16a, 16b) isolated with regard to each other.

An aircraft engine lubrication system has a vortex separator, a first pump line having a first pump, an inlet connected to a separated lubricant area at the outlet end of the separator, and an outlet connectable to the engine. A scavenge line is provided for returning lubricant from the engine to an inlet end of the separator. A lubricant tank is connected in fluid flow communication with the separator by a connection line. A second pump line having a second pump has an inlet connected to the lubricant tank and an outlet connected to the separator for pumping lubricant from the tank to the inlet end of the separator.

The present invention proposes a hardware and software architecture for dynamic modal structural monitoring that uses a robust modal filter to monitor a potentially very large-scale array of sensors in real time, and tolerant of asymmetric sensor noise and sensor failures, to achieve aircraft performance optimization such as minimizing aircraft flutter, drag and maximizing fuel efficiency.

A pneumatic tire for airplanes that assures a good high-speed durability and wear characteristics without its excellent durability against foreign object being impaired is provided. The number of plies of the main belt layer 26 is substantially continuously decreased from the crown center part P0 to the shoulder part, and if the circumferential rigidity in the crown center part P0 of the main belt layer 26 and the circumferential rigidity of the main belt layer 26 at the position P2 which provides ⅔ of the width of the main belt layer 26 are M0 and M2, respectively, the ratio M2/M0 between both is set at a value greater than 0.2 and smaller than 0.8, whereby, while the quantity of materials used for the main belt layer 26 being minimized, the amount of the tread rubber circumferential elongation in the tread central region at the time of air filling to a prescribed internal pressure and at the time of high speed revolution can be efficiently suppressed for suppressing the radial growth of the tire. Because the amount of circumferential elongation of the tread rubber layer 24 is suppressed, and thus the degree of tension of the tread rubber layer 24 is lowered, the resistance to penetration of a foreign object is increased, and even if a foreign object should stick into the tire, the growth of the crack can be suppressed.

The invention discloses a device and a method for assisting airplanes to conduct airline extinguishment. The device is an onboard airline electronic system, comprising a navigation and combustion source sensor, a database system, a voice communication system, a data link, a human-computer interface, a display system, a data interface system and a comprehensive task processing system, wherein all systems are connected with a comprehensive task processing system. The device is utilized to conveniently formulate a flight plan on flying to the scene of fire, an extinguishment strategy flight plan and a round-trip water-drawing flight plan. Meanwhile, the device can monitor and alarm fire behavior display, extinguishment material spray suggestion, extinguishment material spray prediction and extinguishment flight tasks. The method and the device for implementing airline extinguishment researched by the invention can effectively assist pilots to conduct extinguishment, improve extinguishment success rate, save cost, and strengthen safety in the process of executing the tasks.

A preform for a carbon-carbon composite part (55) comprising multiple layers of fibrous mats (51, 52, 53) wherein each of the fibrous mats (51, 52, 53) comprises a random carbon-containing fibrous matrix (11) within which is distributed a polymeric binder and wherein adjacent mat layers (51, 52, 53) are bound together by additional polymer binder, stitching and interlocking tabs. The preform of the present invention may be an aircraft landing system brake disc. Also, a method of manufacturing a thick multi-layer composite preform. The method includes the steps of: providing an optionally reconfigurable tool including a perforated screen through which a vacuum can be drawn; delivering chopped fibers (b), such as pitch fibers, polyacrylonitrile fibers, or mixtures thereof, to said tool while drawing vacuum therethrough, to form a fibrous object; delivering binder (c), for instance in the form of a spray, to said fibrous object; melting or curing said binder (d), for instance by the application of heat or ultraviolet light, to make a fibrous mat (51, 52, 53); assembling, preferably in the substantial absence of cutting or other mechanical modification, a plurality of said fibrous mats (51, 52, 53) and additional binder into the shape of a preform (e); and heat-pressing the resulting mat assembly (f) into a finished thick preform (55).

Aircraft arresting beds at ends of runways may be subject to damaging effects of jet blast phenomena. Arresting units for that and other applications and which are resistant to such effects are described, with related methods.

An improved heating system air pressure sensing port. An example aircraft pitot tube heater uses Positive Temperature Coefficient (PTC) switching thermistors arranged to automatically sense the outside air temperature and heat to a design set point temperature. When a high outside air temperature is experienced, the pitot tube will not turn on. The pitot tube heater only turns on below the design set point and will consumes less current than the standard aircraft pitot tube heaters when operating at very cold temperatures. Virtually no current is drawn when the pitot tube increases past the set point, thus reducing the power drain on the aircraft system. The use of multiple thermistors gives the example pitot tube a level of failure redundancy that is not available in current pitot tube heaters.

An aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades. The main rotor blades are connected to a first annular gear that rotates in a first direction and the counter-rotation blades rotate are connected to a second annular gear that rotates in a second direction that is opposite the first direction for anti-torque. Planetary gears simultaneously drive the first and second annular gear at about the same speed.

An electric charging system for a vessel, vehicle, or aircraft includes one or more energy storage modules on the vessel, vehicle, or aircraft; a pulse rectifier; a converter; and a voltage control transformer. The one or more energy storage modules are connected to outputs of the pulse rectifier. The voltage control transformer is connected to inputs of the pulse rectifier. The voltage control transformer includes a serial transformer having a plurality of pairs of transformer windings, connected together in series, one winding of each pair being adapted to be connected between the pulse rectifier and an input from an energy source and the other winding is connected to the converter.

The invention relates to a kind of bird repellent agent comprising musk ketone: cibetone: muskiness-T: camphor in the weight ratio of 1:1:0.5-1:1.5-3, which can be produced into spray type, powder type and distribution type. The invention does not harm the birds, and can repel birds effectively and reduce the dangers of birds to orchard and airplane effectively, while has the merits of defined scope of bird repellent, long effects, no pollution, easy operation and low cost.

The invention relates to a device for manoeuvring, on the ground, a door of an aircraft landing gear, the door being linked with door manoeuvring means and uplock means for locking the door when it reaches the closed position, at least one unlocking electromechanical actuator arranged to act upon the uplock means with a view to deactivating them during opening of the door in flight. According to the invention, the device comprises control means 17 which can be operated by an operator on the ground in order to control at least:

• • an opening sequence during which the unlocking electromechanical actuator is actuated in order to deactivate the uplock means,
  • a closing sequence during which the manoeuvring means are actuated in order to close the door again.

An aircraft brake assembly comprising a support leg, a main wheel rotatably mounted on the support leg, a brake comprising a first sub-assembly fixed to the main wheel and a second sub-assembly moveably mounted on the support leg and a ground reaction wheel coupled to the second sub-assembly, wherein on application of the brake, the first sub-assembly engages with the second sub-assembly to exert a braking force on the second sub-assembly; and wherein the ground reaction wheel is arranged to transfer the braking force from the second sub-assembly to the ground.

The invention belongs to a flight test-flight technique and relates to a flight simulating method for flight quality and operating characteristics of a transport plane test pilot. The flight simulating method comprises the following steps: taking a certain type of transport plane as a prototype and establishing a dynamic simulating model for different quality characteristics of the transport plane; confirming pneumatic parameters under the quality characteristics according to to-be-simulated different quality characteristics, and resolving an operation response of the airplane in real time according to the pneumatic parameters; performing flight quality modal parameter calibration on the resolved dynamic simulating model for the different quality characteristics, thereby meeting the expected quality and operating characteristics. By utilizing the method provided by the invention, the test pilot can experience a standard and continuous change process of the airplane operation and quality characteristics, so that the evaluating capacity of the test pilot for a task can be promoted; the operation and quality characteristics of the presently simulated airplane can be graphically displayed in real time by combining flight quality standard evaluation indexes; the flight quality level can be directly given; the physical significance is clear; the training for the level evaluation habit of the test pilot is benefited.