101results about "Bird strike avoidance" patented technology

A method and a system for detecting the ingestion of an object by an aircraft turbine engine during a mission is disclosed. The method includes: acquiring during the mission digital images of the operating fan of the turbine engine, these images being acquired at an acquisition frequency proportional to the speed of rotation of the fan and to the number of blades of the fan; identifying the different phases of the mission of the aircraft for each phase of the mission; comparing the images of the fan with at least one reference image corresponding to sound operation of the fan; and, if necessary, identifying each abnormal image of the fan which differs from the corresponding reference image, the identification of an abnormal image of the fan corresponding to the crossing of an alert level for detecting the ingestion of an object by the turbine engine.

The geese chasing system includes of a housing encasing a visual signaling capability, sensor, and audio signaling capability. A plurality of housings can be installed upon the nose and wings of an aircraft in order to direct more signaling strength as well as to accommodate larger aircraft. The geese chasing system also include a cockpit alarm that provides a manual override as well as an automated signaling capability.

The invention relates to a method and a system for detecting the ingestion of an object by an aircraft turbine engine during a mission. The method includes the steps of acquiring during the mission digital images of the operating fan of the turbine engine, these images being acquired at an acquisition frequency proportional to the speed of rotation of the fan and to the number of blades of the fan (E10), identifying the different phases of the mission of the aircraft (E40), for each phase of the mission, comparing the images of the fan with at least one reference image corresponding to sound operation of the fan (E60), and, if necessary, identifying each abnormal image of the fan which differs from the corresponding reference image, the identification of an abnormal image of the fan corresponding to the crossing of an alert level for detecting the ingestion of an object by the turbine engine (E90).

A foreign object damage protection system comprises a sensor for detecting a foreign object, a fluid in a reservoir, a means for dispensing the fluid, the means for dispensing the fluid in communication with the reservoir, and a control unit, whereby when the sensor detects a foreign object, the control unit causes fluid to be dispensed from the reservoir through the means for dispensing and towards the foreign object. The sensor is attachable to one or more locations on an aircraft, such as a wing, nose, windshield, fuselage or tail. The sensor can be a radar sensor, weather radar sensor, weather radar sensor modified to detect objects at short ranges, infra-red sensor, forward-looking infrared sensor, a light detection and ranging sensor, motion sensor, thermal sensor, or video sensor. The system provides a way to protect an aircraft from striking foreign objects, such as birds, in the path of the aircraft.

An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

An aircraft aerodynamic surface includes a torsion box having an upper skin, a lower skin, and a front spar, and a leading edge having an external shell and an impact resisting structure. The external shell may be shaped with an aerodynamic leading edge profile, being configured to provide Laminar Flow Control (LFC) to the leading edge. The impact resisting structure is spanwise arranged between the external shell and the front spar, and is configured for absorbing a bird strike to prevent damage in the front spar. Also, at least one of the external shell and the impact resisting structure is fitted with the upper and lower skins of the torsion box to thereby facilitate leading edge exchange.

A system for reducing damage by birds to an airplane, the system including: (a) a detector mounted on the airplane, operable to detect a bird in a vicinity of the airplane and to generate detection information indicative of motion of the bird; (b) a processor, connected to the detector, configured to analyze the detection information and to selectively trigger activation of a jetting system that is mounted on the airplane in response to a result of the analysis; and (c) the jetting system, operable to jet a high pressure jet onto a bird.

A system operative to protect aircraft and possibly other objects against bird strikes by mounting or disposing a protective components including protective lighting and protective reflective coating on the aircraft, wherein the protective coating is structured to enhance the visibility of the aircraft to birds. The protective lighting and or reflective coating is at least partially disposable in a predetermined location on the aircraft which is commonly observed. A controller is operative with said lighting assembly and configured to perform multi-mode capabilities operative to regulate illumination modes of the lighting assembly. The operative illumination modes are variable and at least partially dependent on a geographical location of the aircraft during flight.

A foreign object damage protection system comprises a sensor for detecting a foreign object, a fluid in a reservoir, a means for dispensing the fluid, the means for dispensing the fluid in communication with the reservoir, and a control unit, whereby when the sensor detects a foreign object, the control unit causes fluid to be dispensed from the reservoir through the means for dispensing and towards the foreign object. The sensor is attachable to one or more locations on an aircraft, such as a wing, nose, windshield, fuselage or tail. The sensor can be a radar sensor, weather radar sensor, weather radar sensor modified to detect objects at short ranges, infra-red sensor, forward-looking infrared sensor, a light detection and ranging sensor, motion sensor, thermal sensor, or video sensor. The system provides a way to protect an aircraft from striking foreign objects, such as birds, in the path of the aircraft.

A protection device includes a flexible laminar body resistant to impacts, arranged separately from the body to be protected and put in the way of the beam of possible trajectories with which a foreign object could impact on the object to be protected, and it includes a plurality of energy absorption elements, provided with device clamping elements over a support structure positioned outside of the beam of possible trajectories, in order for the flexible laminar body to intercept an impact trajectory by the foreign object, resulting in its deformation and the subsequent progressive extension of the energy absorption elements reducing the loads to be supported by the support structure. The protection device is applied to prevent birds or other objects from impacting on sensitive areas of aircraft. The protection device is of a textile nature of reduced weight.

The invention relates to a bird collision prevention protection net of an airplane jet engine. The bird collision prevention protection net is characterized in that the protection net is mainly composed of a metal fixing circular hoop, a conical protection net body, connecting pieces and double helix electric heating wires, and the protection net is installed outside an air inlet of a fairing of the airplane jet engine. The bird collision prevention protection net has the advantages that the situations that a flying bird cracks up an airplane engine and is sucked into the airplane engine are effectively avoided, the structural design is reasonable, and the operability is high; the protection net body is connected with the air inlet of the fairing of the airplane jet engine through the metal fixing circular hoop, and a movable connection mode is adopted, so that maintenance and inspection of the airplane jet engine are facilitated; and the double helix electric heating wires are used for removing or preventing ice which is possibly formed on the conical protection net body in the low-temperature flying process, and the flying safety in the low-temperature environment is guaranteed.

The invention relates to the technical field of spraying mechanisms, and discloses an agricultural spraying mechanism based on Internet of Things intelligent control. The agricultural spraying mechanism comprises an unmanned aerial vehicle body, the side surface of the unmanned aerial vehicle body is fixedly connected with six connecting frames, and the six connecting frames are uniformly distributed on the side surface of the unmanned aerial vehicle body. According to the agricultural spraying mechanism based on intelligent control of the Internet of Things, by arranging the unmanned aerial vehicle body, the connecting frames, a motor box and propellers, spraying irrigation operation and fixed-point irrigation can be conducted in the air, resources are saved, and irrigation cannot be affected by blocking of crops on land; by arranging a high-pressure sprayer, the spraying area of pesticide and irrigation water can be increased, the spraying is more uniform, and meanwhile, part of resources are saved; by arranging a pesticide tank and a water storage tank, pesticide and irrigation water can be separated, errors caused when the pesticide does not need to be sprayed in some areas areprevented, and meanwhile, the pesticide tank and the water storage tank can be cleaned conveniently.

The invention relates to an energy-saving unmanned aerial vehicle with a protection function. The energy-saving unmanned aerial vehicle comprises a main body, a plurality of supporting units, a plurality of signal collecting units, a plurality of flying units, an wind plate rotating mechanism and a protection mechanism, wherein the multiple supporting units are arranged under the main body, the multiple signal collecting units and the multiple flying units are arranged on the main body, and the wind plate rotating mechanism and the protection mechanism are arranged on the main body. The signal collecting units are uniformly distributed on the main body in the circumferential direction. Each signal collecting unit comprises a camera and a wind direction detection unit. The flying units are uniformly distributed on the outer side of the main body in the circumferential direction. The energy-saving unmanned aerial vehicle with the protection function detects the wind direction through the wind direction detection units, according to the flight requirement, the wind plate rotating mechanism is utilized to adjust a wind plate to an appropriate position, and the wind direction is matched, so that the energy resource of flight consumption is reduced, and the practicality of equipment is improved; and besides, whether birds get close and invade or not is detected through the cameras, the protection units rotates flash lamps to be aligned to the birds to flash continuously, accordingly the birds are scared away, and normal flight of the unmanned aerial vehicle is guaranteed.

The present invention is a helicopter lighting system. In particular, the present invention is directed to a helicopter lighting system with light that is directed toward a helicopter's rotors to deter bird strikes. The helicopter lighting system preferably has at least one light mounted on the helicopter's tail aimed at the tail rotor, where illumination from the at least one light comprises ultraviolet light between 300 and 400 nm in wavelength and the at least one light flashes at a pre-determined frequency, preferably between 1 Hz and 3 Hz. The light system further preferably comprises at least one roof light mounted on the roof, where illumination from the roof light shines on the main rotor and vertical shaft of the helicopter. The lighting system also preferably has a belly light mounted on the belly of the helicopter.

The invention discloses an anti-collision board and a manufacturing method thereof. The anti-collision board comprises a colliding layer, a buffer layer and an energy-absorbing layer, wherein the buffer layer is located between the colliding layer and the energy-absorbing layer; the buffer layer comprises two or three aramid honeycomb layers which are bonded via functional resin; each aramid honeycomb layer is made of an aramid composite material and has a thickness of 5 to 10 mm; the colliding layer is made of aramid fiber and bonded with the buffer layer via the functional resin; and the energy-absorbing layer is made of a high-molecular polymer and bonded with the buffer layer via the functional resin. The anti-collision board provided by the invention employs a totally-nonmetal anti-collision energy-absorbing structural board body, is light, has good energy-absorbing and anti-collision effect, can effectively protect the inner structures of a fuselage and reduces later maintenance cost for an airplane.

A support device for a radio equipment of an aircraft, radio system and aircraft are provided. The support device includes a fastening structure (31), intended to be secured to a lower surface of a fuselage of an aircraft, and a support platform (33) of the radio equipment (25). The support platform (33) is mounted pivoting on the fastening structure (31) around a pivot axis (A) between an operational position and a backup position. The support device comprises a locking mechanism (56), able to be actuated from a locked configuration, in which said locking mechanism (56) keeps the support platform (33) in its operational position while preventing any pivoting of the support platform (33), to an unlocked configuration, in which the locking mechanism (56) allows the support platform (33) to pivot relative to the fastening structure (31).

The present invention is an aircraft lighting system. In particular, the present invention is directed to an aircraft lighting system with light that is directed toward an aircraft's engines to deter bird strikes. The lighting system for a jet-powered aircraft has at least one light mounted on an aircraft fuselage aimed at an engine inlet of an engine nacelle of the aircraft. The illumination from the light comprises ultraviolet light between 300 and 400 nm in wavelength and the light flashes at a pre-determined frequency preferably between 1 and 3 Hz. Additional lights can be mounted on the engine nacelles to illuminate outer engine nacelles. Preferably, the engine of the aircraft also has blades coated in fluorescent or iridescent paint to increase the reflectivity of the blades to further illuminate the blades of the engine. The lighting system preferably automatically illuminates the engine inlets during take-off and descent.

A method, apparatus, and system for automating detection and avoidance for an aircraft. A process activates a set of lamps visible on an exterior of an aircraft to emit light. The process modulates an intensity of light from the set of lamps at a set of frequencies that is detectable by a remote collision avoidance system in a remote aircraft during flight. The light from the set of lamps at the set of frequencies is perceived as continuous by a person looking at the aircraft in a sky, reducing visibility of the aircraft in the sky.

A method for inspecting impacts present on an internal face of a fan casing, the method including: spotting a first impact present on the internal face of the fan casing; delimiting an inspection area containing the first impact; spotting the various impacts present in the delimited inspection area, the various spotted impacts forming a set of impacts to be considered; measuring, for each impact that is to be considered, the depth of length of the impact; for each impact to be considered, determining a harmfulness value, using at least one chart relating the depth and length of each impact to be considered to a level of harmfulness; determining, for the inspection area containing the first impact, a total harmfulness value by adding together the harmfulness level determined for each impact to be considered.

The invention relates to the technical field of unmanned flight vehicles and in particular relates to an unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage, wherein the fuselageis provided with vehicle arms; a first motor is arranged at a free end of each vehicle arm; a rotor wing is arranged on an output shaft of each first motor; the fuselage is further provided with a control module; the control module comprises a controller and an attitude sensor; the controller is in signal connection with the motors and the attitude sensor; the controller can be used for controlling the rotation of the motors according to data of the attitude sensor; air injection devices are uniformly arranged in the peripheral direction of the fuselage; the attitude sensor comprises a gyroscope and an acceleration sensor; the controller can be used for detecting attitude data of the fuselage according to the data of the gyroscope; the controller is used for controlling the air injectiondevice to carry out air injection according to the data of the attitude sensor. The unmanned aerial vehicle provided by the invention can rapidly get away from and dispel bird flocks when meeting thebird flocks.

The invention relates to the field of aircraft structure design, in particular to an aircraft leading edge anti-bird collision structure. At present, the bird impact resistance design and installationstructure of the leading edge structure is complex, the structure efficiency is low, the weight of the structure is large, and the effective space is affected. A lead edge bird impact resistant structure of that aircraft comprises a leading edge skin and a rib plate, and a hollow thin-wall energy absorb tube is arranged in the cavity of the leading edge skin at a distance from the leading edge skin. The invention has the advantages of simple structure, simple installation, high structure efficiency and low weight cost.

A protection device includes a flexible laminar body resistant to impacts, arranged separately from the body to be protected and put in the way of the beam of possible trajectories with which a foreign object could impact on the object to be protected, and it includes a plurality of energy absorption elements, provided with device clamping elements over a support structure positioned outside of the beam of possible trajectories, in order for the flexible laminar body to intercept an impact trajectory by the foreign object, resulting in its deformation and the subsequent progressive extension of the energy absorption elements reducing the loads to be supported by the support structure. The protection device is applied to prevent birds or other objects from impacting on sensitive areas of aircraft. The protection device is of a textile nature of reduced weight.

An airfoil (10) having a main structure (15) including at least one spar (16) and a front structure (20) forming a leading edge (21), said airfoil (10) having an empty space (25) between said main structure (15) and said front structure (20). The airfoil (10) includes a rigid deflector member (30) in said empty space (25), the deflector member being fastened to the main structure (15), said deflector member (30) having a sharp edge (31) facing towards said front structure (20) in order to deflect an external obstacle impacting against said front structure (20).

An airfoil (10) having a main structure (15) including at least one spar (16) and a front structure (20) forming a leading edge (21), said airfoil (10) having an empty space (25) between said main structure (15) and said front structure (20). The airfoil (10) includes a rigid deflector member (30) in said empty space (25), the deflector member being fastened to the main structure (15), said deflector member (30) having a sharp edge (31) facing towards said front structure (20) in order to deflect an external obstacle impacting against said front structure (20).

The invention relates to an intelligent unmanned aerial vehicle having a self-protecting function. The intelligent unmanned aerial vehicle comprises a main body, a plurality of supporting units arranged under the main body, a plurality of signal acquisition units arranged on the main body, a plurality of flight units, as well as a direction adjusting mechanism and a protecting mechanism arranged on the main body, wherein the signal acquisition units are uniformly distributed on the main body in the circumferential direction, and each signal acquisition unit comprises a camera and a wind direction measuring unit; and the flight units are uniformly distributed on the outer side of the main body in the circumferential direction. According to the intelligent unmanned aerial vehicle having the self-protecting function disclosed by the invention, the wind direction is detected by the wind direction measuring units; according to the flight requirements, a flat plate is adjusted by the direction adjusting mechanism to an appropriate position, and the direction of wind power is matched, so that the energy resources consumed by flight are reduced, and the practicality of the equipment is improved; and moreover, the situation whether birds get close to and attack the unmanned aerial vehicle is detected by the cameras, flash lamps rotate through protecting units to aim at the birds and perform continuous gleaming, so that the birds are scared off, and the normal flight of the unmanned aerial vehicle is guaranteed.

The present invention is an aircraft lighting system. In particular, the present invention is directed to an aircraft lighting system with light that is directed toward an aircraft's engines to deter bird strikes. The lighting system for a jet-powered aircraft has at least one light mounted on an aircraft fuselage aimed at an engine inlet of an engine nacelle of the aircraft. The illumination from the light comprises ultraviolet light between 300 and 400 nm in wavelength and the light flashes at a pre-determined frequency preferably between 1 and 3 Hz. Additional lights can be mounted on the engine nacelles to illuminate outer engine nacelles. Preferably, the engine of the aircraft also has blades coated in fluorescent or iridescent paint to increase the reflectivity of the blades to further illuminate the blades of the engine. The lighting system preferably automatically illuminates the engine inlets during take-off and descent.

An airframe leading edge part designed to be replaceable fixed to a structural portion which during use moves through the air. The airframe leading edge part includes first and second longitudinal joint edges adapted to fit the structural portion. At least one joint is provided between the structural portion and at least one of the longitudinal joint edges. The joint is adapted to break in the event of a object strikes and deforms the airframe leading edge part during use. The joint is designed to break at beforehand determined maximum joint strength of the joint. Also a repair method for exchanging a damaged leading edge.

A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and / or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.

An automatic emergency radar and proximity sensor activated protection system that could assist to prevent commercial, private, or military aircraft jet engines from being damaged or destroyed.This is accomplished by the installment of a Shielding Blade Assembly which will immediately close when detection of objects such as; birds, debris, or other destructive elements try to enter through the engine intake while the aircraft is in FLIGHT.When the Shielding Blade Assembly is closed, an Internal Air Injection Unit (A.I.U.) will supply high volumes of air in order for the engine to stay operational and prevent it from stalling while in FLIGHT.Pilot and crew can then take all the necessary precautionary steps required until the aircraft with passengers and / or cargo can safely reach and land at the nearest available airport.

A real-time aircraft bird congestion indicator system for measuring congestion in an airspace between aircraft and birds uses one or more radars to continuously survey an airspace around an airport or aerodrome and continuously generate aircraft tracks and bird tracks in the airspace. A congestion processor connected to the radar(s) receives the aircraft and bird tracks and processes them to periodically generate a congestion indicator that measures the congestion in the airspace. A display processor connected to the congestion processor receives the congestion indicator which is updated periodically by the congestion processor and displays the congestion indicator to a user, generates an alert if the congestion indicator falls outside set operating limits, and / or sends the congestion indicator or alert to another system.