19results about "Bird strike avoidance" patented technology

A counter-bird aircraft system is disclosed, including a Doppler detection device having at least one emitter positioned on an aircraft, the emitter to emit a beam ahead of the aircraft. At least one receiver detects a return signal caused by the presence of a threat to the aircraft. A microprocessor processes the reception of the return signal and transmits an alert to an alert system which notifies the pilot of the presence of the threat.

The invention relates to the technical field of aerospace structure safety, and discloses a flying bird anti-collision device with a foamed aluminum sandwich energy-absorbing structure, the flying bird anti-collision device comprises an assembly frame and an outer frame as the device, the corners of the outer side of the assembly frame are provided with assembly cylinders, and the assembly frame is assembled in the head of an aircraft through the assembly cylinders; the front panel is arranged on the inner side of the assembly frame and is used for bearing a first collision impact; the buffering assembly is arranged on the inner side of the assembling frame and used for buffering the first impact; the sandwich board is arranged on the inner side of the assembly frame and used for bearing the buffered impact; and the rear panel is arranged on the inner side of the assembly frame and is used for bearing the impact which is buffered twice. Through ordered hierarchical arrangement of the front panel, the buffer assembly, the foamed aluminum sandwich panel and the rear panel, a synergistic energy absorption system and a multi-structure synergistic gradient protection mechanism are constructed, impact is decomposed into a plurality of controllable energy dissipation stages, and efficient management and dissipation of impact energy are achieved.

A support device (1) for a stator blade (22) of an aircraft turbomachine with longitudinal axis (X) comprising an external wall (21) from which the stator blade (22) projects, the support device (1) comprising: - a housing (2) configured to radially receive a mounting foot (23) of the stator blade (22); - an upstream support foot (5) and a downstream support foot (6) connected respectively to an upstream end (3) and a downstream end (4) of the housing (2) and configured to be mounted on the external wall (21) of the aircraft turbomachine; the downstream support foot (6) comprising a cavity in which is mounted a shock indicator (10) configured to change its visual appearance irreversibly in the event of deformation of a contour (9) of predetermined shape of the cavity, so as to visually detect an impact exerted on the stator blade (22). Figure from the summary: Figure 2

An aircraft engine alert system and associated method are disclosed. The aircraft engine alert system includes an aircraft including at least one engine having an engine inlet. The aircraft engine alert system also includes a sensor that is coupled to the engine. The sensor is configured to detect a movable object and determine a distance between the movable object and the engine inlet. The aircraft engine alert system further includes an alert generating device in electrical communication with the sensor and configured to issue an alert to the movable object when the engine is in use and when the movable object is within a predetermined range of the engine inlet.

A spatially staggered emergency strut system is disclosed. A strut system for a wing of an aircraft includes a strut member extending from the wing and a first emergency strut assembly associated with the wing. The first emergency strut assembly includes a first emergency strut and a second emergency strut, a first end of the first emergency strut connected to the strut member, a first end of the second emergency strut connected to the strut member, wherein second ends of the first emergency strut and the second emergency strut are each connected to the wing spaced apart from each other in a direction of a chord.

The invention relates to the technical field of waterproof engineering, in particular to a wind power blade surface defect detection technology based on image processing, which comprises a machine body, the bottom of the machine body is provided with a marking assembly, and the marking assembly comprises a control mainboard. According to the wind power blade surface defect detection technology based on image processing, a marking assembly is added, a main board can be controlled to be connected with a camera, an image input by the camera is compared through image recognition software connected with a cloud end, and a first rotating motor can drive a rotating shaft to rotate; meanwhile, the direction of the electric spray head can be adjusted along with the direction of the electric spray head, the electric spray head is connected with fluorescent paint in a storage box through a communicating pipe, when defects are found, the electric spray head sprays out the paint, and a trapezoidal baffle can prevent the paint from adhering to a camera; and the paint is found and then compared with the comparison picture, so that the defect can be found more quickly for remedy, and the convenience is improved.

A reinforced leading edge section for an aircraft, including an outer skin formed with an aerodynamic leading edge profile, an inner reinforcement arranged internally with respect to the outer skin along the span of the leading edge section, wherein the inner reinforcement includes a base with a C-shaped configuration joined to the outermost part of the outer skin, and a web having a free end and an opposite end joined to the base, the web extended in a direction transverse to the direction of the span of the leading edge section.

This invention relates to the field of aircraft structural design technology, specifically to a leading-edge tower-type bird strike protection structure for aircraft. It includes a leading-edge skin assembly, a first protective assembly, a second protective assembly, a third protective assembly, and a rear beam assembly. The leading-edge skin assembly and the rear beam assembly are located at the front and rear ends of the sequentially connected first, second, and third protective assemblies, respectively, and are wrapped around them. The rear end of the first protective assembly is fixedly connected to the front end of the second protective assembly and is used to resist high-speed bird impacts. The rear end of the second protective assembly is fixedly connected to the front end of the third protective assembly and is used to resist medium-speed bird impacts. The rear end of the third protective assembly is fixedly connected to the rear beam assembly and is used to resist low-speed bird impacts. The purpose of this leading-edge tower-type bird strike protection structure is to solve the problem of low structural efficiency in existing aircraft leading-edge bird strike protection structures.

An assembly for aircraft to prevent bird strikes by deterring the birds using an 18 kHz signal. The assembly can be installed on the front of the aircraft. Each assembly includes a radio transmitter configured to generate an 18 kHz signal with a 5-10-mile range.

An aircraft provided with a transparent wall interposed between an internal environment located in the aircraft and an external environment, the transparent wall being fixed to a supporting structure of the aircraft by a fixing system, the transparent wall having an internal face facing the internal environment and an external face facing the external environment. The fixing system comprises at least one martyr energy-absorbing pad, the energy-absorbing pad comprising at least one energy absorber connected to the transparent wall and to the supporting structure, the at least one energy absorber comprising an internal absorber attached against the internal face.

The present invention relates to an aircraft (1) equipped with a transparent wall (10) interposed between an internal environment (INT) located in the aircraft (1) and an external environment (EXT), the transparent wall (10) being fixed to a supporting structure (5) of the aircraft (1) by a fastening system (20), the transparent wall (10) having an inner face (11) facing the internal environment (INT) and an outer face (12) facing the external environment (EXT). The fastening system (20) comprises at least one sacrificial energy-absorbing pad (30), said energy-absorbing pad (30) comprising at least one energy absorber connected to the transparent wall (10) and to the supporting structure (5), said at least one energy absorber comprising an internal absorber (40) attached to the inner face (11). (Shorthand figure: Figure 2)

The invention relates to the technical field of aircrafts, in particular to a combined type vertical take-off and landing aircraft, and solves the problems that a remote control type fixed wing aircraft is poor in flexibility and birds or foreign matters in the birds may impact a main power propeller in the parallel flight process of equipment. Comprising a remote control type fixed-wing aircraft. Through the four propellers facing upwards, the remote control type fixed-wing aircraft can vertically take off and land, and after the equipment starts to fly in parallel in the half air, the propellers originally facing upwards can be adjusted to face backwards through the angle adjusting mechanism, so that the overall flying speed of the equipment is increased, and the flying speed of the equipment is improved. And when the equipment flies in parallel in the air, a layer of protective net can be manufactured on the outer side of the main power propeller through the power propeller protective mechanism, the main power propeller serving as a main power source can be prevented from colliding with external foreign matter through the protective net, and by means of the technical scheme, the flexibility of the equipment is improved, and meanwhile the service life of the equipment is prolonged. And the safety is improved.

The invention relates to the field of temperature sensors, in particular to a dual-redundancy air inlet temperature sensor for preventing ice and bird impact. Comprising a sensitive element, a body and an extension part, the extension part is provided with a first detection cavity and a second detection cavity; the first detection cavity and the extension part form a first channel for detection, a second channel for air inlet and a third channel for air outlet; the second detection cavity and the extension part form a fourth channel for detection, a fifth channel for air inlet and a sixth channel for air outlet; the third channel is located in the outline of the extension part and communicates with the first detection cavity and the second detection cavity. According to the dual-redundancy air inlet temperature sensor for preventing icing and bird impact, air can still continue to flow through the third path after the dual-redundancy air inlet temperature sensor is impacted by birds and the sixth channel is completely blocked, the reliability of the dual-redundancy air inlet temperature sensor for preventing icing and bird impact is higher, and the risk of aviation aircrafts is reduced.

The present invention relates to an aircraft (1) equipped with a transparent wall (10) interposed between an internal environment (INT) located in the aircraft (1) and an external environment (EXT), the transparent wall (10) being fixed to a supporting structure (5) of the aircraft (1) by a fastening system (20), the transparent wall (10) having an inner face (11) facing the internal environment (INT) and an outer face (12) facing the external environment (EXT). The fastening system (20) comprises at least one sacrificial energy-absorbing pad (30), said energy-absorbing pad (30) comprising at least one energy absorber connected to the transparent wall (10) and to the supporting structure (5), said at least one energy absorber comprising an internal absorber (40) attached to the inner face (11).

In one aspect, a device for preventing bird strikes to an engine. The device includes a projector mounted on a component of the engine. The projector is positioned to project an image outside of the engine. In another aspect, an engine for an aircraft. The engine includes an engine component and a projector mounted on the engine component. The projector is positioned to project an image outside of the engine.

The system (10) comprises a casing (12) having an outer surface (12a) and an inner surface (12b), internally defining a cavity (14), and comprising a front portion (20) susceptible of undergoing a collision with a striking mass (M) and being penetrated and crossed by the latter. There is an assembly (22) for absorbing impacts, situated in the cavity (14) downstream of the front portion (20). The assembly (22) comprises a cloth (24; 26; 28) separate and spaced apart from said front portion (20), joined to the inner surface (12b) of the casing (12), and configured to be hit by the striking mass (M) crossing the front portion (20), so as to envelop and contain the striking mass (M) in order to absorb the energy resulting from the collision. The cloth (24; 26; 28) has its periphery (24a, 24b; 26a, 26b; 28a, 28b) glued in a distributed manner to the inner surface (12b) of the casing (12). Furthermore, the cloth (24; 26; 28) is loose and can freely unfurl in the cavity (14).

Described herein is an aircraft. The aircraft includes a peripheral assembly, such as a sensor probe. The aircraft further includes a release assembly connecting the peripheral assembly to a portion of the aircraft. The release assembly is configured to separate the peripheral assembly and the portion upon receipt of a threshold force. The release assembly may be configured to allow for the quick release, such as via a snap-fit connection, between the peripheral assembly and the portion of the aircraft.

The invention relates to the technical field of aircrafts, in particular to a three-axis rotor composite wing aircraft which comprises a fuselage, tilting rotor modules are arranged on the left side and the right side of the head of the fuselage, each tilting rotor module comprises a duct rectifying cylinder located on one side of the head of the fuselage, and a tilting mechanism used for making the duct rectifying cylinders tilt is arranged on the fuselage. A first rotor wing body is mounted in the duct rectifying cylinder; a plurality of connecting shafts are evenly distributed at the inlet end of the duct rectifying cylinder in the circumferential direction, and a main stop lever is fixed to each connecting shaft. By arranging the connecting shaft and the main stop lever, in the level flight cruising stage, the inlet end of the duct rectifying cylinder can be partially shielded and protected, the effective area capable of being impacted by flying birds is remarkably reduced, and the collision probability of the first rotor wing body and the birds is greatly reduced; moreover, compared with a totally-closed protection device, the self weight of the aircraft can be obviously reduced, and the influence on the cruising ability and the loading capacity is reduced to the maximum extent while the safety is improved.

An optical foreign object detection (FOD) system for a gas turbine engine includes a multiple of emitters (82) arranged about an inner periphery of a fan cowl, a multiple of receivers (84) arranged about the inner periphery of the fan cowl, each of the multiple of receivers (84) receiving a beam from one of the multiple of emitters (82) to form a beam matrix (88); and a control system (86) in communication with the multiple of emitters (82) and the multiple of receivers (84), the control system (86) operable to detect a minimum sized object in response to breaking at least one beam of the beam matrix (88).