36 results about "Landing lights" patented technology

A multi-mode visible and infrared lighthead (100) for use as a landing light or searchlight. The multi-mode lighthead incorporates a modular design wherein at least one visible light source (200) and at least one infrared diode (302) are mounted into the rear sector (128) of a housing (102). Visible or infrared light is emitted out of the front sector (122) of the housing (102). Lenses (308) are installed onto the front sector (122) of the housing (102) and sealed to protect the interior of the lighthead (100) from the elements. Alternatively, and in combination, an imaging module (1), and infrared laser (400) and / or a fixed-position searchlight with rangefinder and positioning capability is provided in the multi-mode lighthead(100).

A light module (1) suitable for use as a landing light for an airplane is disclosed, using an elongated array (2) of light emitting diodes (LEDs) as the light source. Light from the LEDs is directed toward a transparent cover (3). The cover (3) may include a plano-convex lens (4) at its center for nominally collimating the light from the LEDs. The cover (3) may also include a generally featureless peripheral region laterally circumferentially surrounding the lens (4). A faceted reflecting surface (6) having a generally parabolic base curvature (8) may extend circumferentially around a longitudinal axis of the landing light from the LEDs to the cover (3). Light exiting the LEDs at a relatively high angle of exitance reflects off the faceted reflecting surface (6) and transmits through the generally featureless peripheral region of the cover (3).

Onboard systems and methods for detection of airborne volcanic ash. One or more cameras are added to an aircraft. Each camera is configured to view a volume of air illuminated by a standard aircraft light, such as a strobe warning light (e.g., located on a wing tip) or a forward-facing landing light (e.g., located in the nose). Each camera is connected to a data processor. When diffuse volcanic ash is present, it scatters light transmitted from the standard aircraft light. Each camera converts impinging backscattered light into digital data which is sent to the processor. The processor processes the data from the camera or cameras to derive a measurement of the backscattered light and issues an alert when the amount and type of backscatter are compatible with the presence of volcanic ash.

An electronically controlled retractable landing light (100) for use with aircraft. A controller (106) compares the commanded position of a lighthead (108) by means of a contactless absolute position sensor (212). Operation of a brake (111), motor (110), and lamp (112) is controlled by a control unit (210). Electrical power to the brake (111), motor (110), and lamp (112) is slowly applied and removed to reduce electromagnetic emissions and extend the service life of a power stage (208), brake (111), motor (110), and lamp (112). The lighthead (108) may be manually stowed in the event of a fault.

An LED landing light arrangement for an aircraft comprises a plurality of LED light sources (12,14,16) for arrangement on an aircraft (24), primarily on the wing roots (20), on the front edges of the wings (22) and / or on the landing gears (18). The LED light sources (12,14,16) are operative to generate, relative to the central axis of the aircraft (24), a light distribution (10) ahead of the aircraft (24) that is spread substantially in a Y-shaped configuration in an obliquely downward direction. The light distribution (10) comprises two converging lateral regions (34,36) arranged laterally ahead of the aircraft (24), and a central region (40) running from said converging lateral regions (34,36) along an extension of said central axis and oriented in a direction away from the aircraft (24).

An assembly for accessing a body cavity having an illuminated proximal end. The assembly includes a housing defining a longitudinal axis and having a longitudinal opening therethrough for receiving a surgical object, an illumination source disposed adjacent a proximal end of the housing and a sensor mechanism disposed along the longitudinal opening and operably connected to the illumination source. The sensor mechanism is configured to detect the presence of a surgical object within the longitudinal opening and deactivate the illumination source when a surgical object is present in the longitudinal opening.

The invention discloses a landing lamp and taxi light debugging and calibration system and method. The system comprises an interface mounting seat, a laser generator and a main control device. The interface mounting seat is mounted on a landing lamp and sliding lamp cover through an adjusting member, and the laser generator comprises a first microprocessor, a driver, a laser generator, an angle measuring module and a first communication module, wherein the driver, the laser generator, the angle measuring module and the first communication module are each connected to the first microprocessor.The laser generator is connected with the driver, and the main control device comprises a second microprocessor, a second communication module and a human-machine interaction module, wherein the second communication module and the human-machine interaction module are connected with the second microprocessor. The angle measuring module and the laser generator are fixedly arranged. The system makesit unnecessary for a calibration worker to select the night and to be able to perform the lighting debugging and calibration of a landing light and a taxi light without turning on the landing light and the taxi light, and also avoids the disadvantages of an operator being burned by the landing light and the taxi light.

An electronically controlled retractable landing light ( 100 ) for use with aircraft. A controller ( 106 ) compares the commanded position of a lighthead ( 108 ) by means of a contactless absolute position sensor ( 212 ). Operation of a brake ( 111 ), motor ( 110 ), and lamp ( 112 ) is controlled by a control unit ( 210 ). Electrical power to the brake ( 111 ), motor ( 110 ), and lamp ( 112 ) is slowly applied and removed to reduce electromagnetic emissions and extend the service life of a power stage ( 208 ), brake ( 111 ), motor ( 110 ), and lamp ( 112 ). The lighthead ( 108 ) may be manually stowed in the event of a fault.

This invention relates to a system for controlling and monitoring visual landing lights based on CAN bus, which is a distance digital signal communication system for airport visual landing lights disclosing an indoor No.0 node including a CPU, a CAN bus module, an input module, an echo module, a serial communication module and a monitor module, several outdoor nodes of branch lamp boxes are also disclosed, all modes are parallel hung on KVV armored cable via CAN drive interface.

A light module (1) suitable for use as a landing light for an airplane is disclosed, using an elongated array (2) of light emitting diodes (LEDs) as the light source. Light from the LEDs is directed toward a transparent cover (3). The cover (3) may include a plano-convex lens (4) at its center for nominally collimating the light from the LEDs. The cover (3) may also include a generally featureless peripheral region laterally circumferentially surrounding the lens (4). A faceted reflecting surface (6) having a generally parabolic base curvature (8) may extend circumferentially around a longitudinal axis of the landing light from the LEDs to the cover (3). Light exiting the LEDs at a relatively high angle of exitance reflects off the faceted reflecting surface (6) and transmits through the generally featureless peripheral region of the cover (3).

An LED landing light arrangement for an aircraft comprises a plurality of LED light sources (12,14,16) for arrangement on an aircraft (24), primarily on the wing roots (20), on the front edges of the wings (22) and / or on the landing gears (18). The LED light sources (12,14,16) are operative to generate, relative to the central axis of the aircraft (24), a light distribution (10) ahead of the aircraft (24) that is spread substantially in a Y-shaped configuration in an obliquely downward direction. The light distribution (10) comprises two converging lateral regions (34,36) arranged laterally ahead of the aircraft (24), and a central region (40) running from said converging lateral regions (34,36) along an extension of said central axis and oriented in a direction away from the aircraft (24).

An automatically adjustable landing light circuit and method for an aircraft approaching a target are provided. The circuit includes a memory having therein an auto adjustable landing light program, and a processor operationally coupled to a source of real-time navigation data, a source of intended approach information, a source of target geometry, and a source of environmental information including cross-wind data. The processor executes the auto adjustable landing light program, to: determine a course correction, as a function of the cross-wind data, upon determining each occurrence of deviations exceeding respective thresholds for the current heading and an intended heading, the current pitch and an intended pitch, and the current yaw and an intended yaw. The processor generates control motor commands for a landing lights assembly that generates a landing light projection. The control motor commands adjust the landing light projection in accordance with each determined course correction.

The invention relates to a landing lamp test device, system and method and a storage medium, and belongs to the technical field of lamp test, and the device comprises a locking device, a vibration generation device, a jitter detection device, a displacement detection device, a deformation detection device and a looseness detection device. The locking device is used for fixedly mounting the landing lamp and the mounting structure thereof according to a standard and then locking the landing lamp and the mounting structure thereof on the test bed; and the vibration generating device is used for providing vibration and the like for the landing lamp and the mounting structure of the landing lamp during normal navigation of an airplane through the test bed. Through orderly matched starting of the locking device, the vibration generation device, the jitter detection device, the displacement detection device, the deformation detection device and the looseness detection device, defects existing in the landing lamp mounting structure can be rapidly tested and positioned, and the potential safety hazards can be eliminated in the test process; and the test blank of the section is filled.

A helicopter of the type having an electrical system, a landing light, a master switch and a power supply of between about 18-32 V for operating the electrical system when the master switch is in an on position also includes a landing light fault detector. The landing light fault detector includes a light switch for turning the landing lights on and off and circuit means for detecting a fault in the landing light and for providing a signal indicative of a fault whether or not the light switch is in an on or off position.

A helicopter of the type having an electrical system, a landing light, a master switch and a power supply of between about 18-32 V for operating the electrical system when the master switch is in an on position also includes a landing light fault detector. The landing light fault detector includes a light switch for turning the landing lights on and off and circuit means for detecting a fault in the landing light and for providing a signal indicative of a fault whether or not the light switch is in an on or off position.

A method for providing landing lights operation data during a flight of an aircraft is provided. The method obtains a standard operating procedure (SOP) for operating landing lights onboard the aircraft during the flight, wherein the SOP comprises a customary industry-recommended practice for at least one of extension and retraction of the landing lights on the aircraft, and wherein execution of the SOP produces a flight efficiency level including at least fuel burn and drag parameters; determines an optimized operating procedure for the landing lights to increase the flight efficiency level to achieve an increased flight efficiency level, based on real-time contextual data; and presents an advisory comprising at least graphical elements associated with the optimized operating procedure, a potential cost savings for the optimized operating procedure, and the increased flight efficiency level onboard the aircraft, via a display device.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle undercarriage which comprises a plurality of supporting legs, and any supporting leg comprises a buffering energy absorber and a foot stool; one end of the buffer energy absorber is connected with an unmanned aerial vehicle, and the other end is connected with the foot stool; and the buffer energy absorber comprises elastic pieces and a damping layer, and the damping layer is clamped between the two elastic pieces. The unmanned aerial vehicle undercarriage is simple in process, low in cost and light in weight, has good buffering and energy absorbing characteristics and can be applied to vertical take-off and landing light unmanned aerial vehicles on a large scale.

The invention discloses an angle-adjustable retracting and stretching mechanism of an angle-adjustable landing light. The angle-adjustable retracting and stretching mechanism comprises a shell, a sector gear component, a motor reducer, a swinging arm component, a stretching in-place switch and a retracting in-place switch. The sector gear component is fixed to the shell through a main shaft to be connected with the shell in a rotating mode and is provided with a load fixing end. An output gear of the motor reducer is meshed with the sector gear component to drive the sector gear component to rotate. The swinging arm component comprises an upper swinging arm and a lower swinging arm, the upper swinging arm and the lower swinging arm are driven by the sector gear component to rotate around the main shaft, the upper swinging arm is provided with a stretching in-place contact piece, the lower swinging arm is provided with a retracting in-place contact piece, and an adjusting screw is installed on the lower swinging arm and abuts against the side wall of the upper swinging arm. The stretching in-place switch is fixed to the shell and matched with the stretching in-place contact piece of the upper swinging arm. The retracting in-place switch is fixed to the shell and matched with the retracting in-place contact piece of the lower swinging arm. The angle-adjustable retracting and stretching mechanism has the advantages of being high in reliability, easy to maintain, small in size and light in weight, enabling the complete-stretching angle to be conveniently adjusted and the like.

The invention discloses a target correcting device for landing and taxi light mounting. The target correcting device comprises a single-light optical adjusting device, the single-light optical adjusting device is used for adjusting the light beam center of a light source module of a single landing light / taxi light in the assembling process, the single-light optical adjusting device is provided with an adapter plate which is completely the same as the actual product installation position of the landing light / taxi light, and the adapter plate is used for arranging the light source module in relatively-open space, so that the position of the light source module is adjusted according to the adjustment condition in the adjustment process. The target correcting device has the beneficial effect of avoiding the situation that light sources are different due to different batches, processing errors and assembling errors exist in light source printed boards and light reflecting bowls, and consequently light spots of the landing light / taxi light are different.

The invention discloses an aviation landing lamp folding and unfolding adjustment driving device and application. The aviation landing lamp folding and unfolding adjustment driving device is used for controlling folding and unfolding of an aviation landing lamp. The aviation landing lamp folding and unfolding adjustment driving device is composed of a device shell, a two-stage worm and worm gear pair, a driving motor, a gear assembly, a rack assembly, an angular displacement sensor and the like. The device has the beneficial effects that the structure is compact and reasonable, the space requirement is small, work is reliable, and the aviation landing lamp folding and unfolding adjusting function under the small space size can be achieved.

The invention discloses a novel elevator call-out controller comprising a microprocessor module, an input module, an output module, a communication module and a power module, wherein the microprocessor module is an STM32 chip; the input module comprises uplink input and downlink input; the output module comprises floor display output, floor landing light output and uplink and downlink instructionlight output; the communication module is a CAN communication circuit; and the power module is used for providing power for the whole controller. The novel elevator call-out controller disclosed by the invention has the advantages of simple structure, advanced design, and high real-time controllability, response speed and security; meanwhile, the number of peripheral components and the productioncost are reduced, and the novel elevator call-out controller is more suitable for mass production, and can be used for many small and medium-sized elevator enterprises.

The embodiment of the invention discloses a light source structure of an aviation landing lamp. The light source structure comprises a light source shell, a light source assembly, a cover plate assembly, a radiator assembly and a driver assembly. In the light source shell, a shell substrate and shell side plates form an open type light source cavity used for installing a light source assembly, and the light source assembly is sealed through a cover plate assembly. The radiator assembly comprises at least two rows of radiating fins which are vertically arranged, and a middle partition area is arranged between every two adjacent rows of radiating fins. The driver assembly comprises a driver body and a driver supporting column, and the driver supporting column is fixedly connected to the driver screw installation hole of the shell substrate through a fixing screw so that the driver assembly can be fixedly installed on the side, provided with the radiator assembly, of the light source shell. According to the embodiment of the invention, the problem that the service life of a landing lamp product is shortened due to the fact that the lighting effect of an existing aviation LED light source is damaged due to temperature rise is solved.

A helicopter landing indicator light in the field comprises a casing, a light-emitting component, a control circuit board and a transparent upper cover. After the battery is installed, the light-emitting component can emit light under the control of the control circuit board. Wherein, the light emitted by the visible light emitter is used for illumination, and the infrared light emitted by the infrared emitter is used for indicating the position. Since the infrared light needs to be equipped with specific equipment to be observed, it can prevent the above-mentioned helicopter field landing indicator light from being discovered by others. In addition, the light-emitting component and the control circuit board are accommodated in the accommodation cavity formed by assembling the casing and the transparent upper cover, so that the above-mentioned helicopter field landing indicator light has a compact structure and a small volume, and is difficult to be found in the field. Therefore, the above-mentioned helicopter field landing indicator light has effectively improved the concealment.

The invention provides a light simulation teaching and training system for an aircraft. The system comprises an electrical control component and an engine body. The engine body comprises a cockpit skin, a passenger cabin skin, an anti-collision light component, a passenger cabin top frame, a cockpit roof, a cockpit bottom frame cover plate, a passenger cabin right frame, a passenger cabin left frame, a warehouse simulation cabin, a warehouse cabin door, a cockpit bottom frame, a wing ice-detecting light, a simulation wing, a simulation tail wing, a flight logo light component, a wing light component, a front support ring, a rear support ring, a landing light component, a passenger cabin light component, a passenger service component, an instrument display simulation component, a passenger cabin roof, a passenger cabin right frame cover plate, a passenger cabin left frame cover plate, a passenger cabin emergency light component, a chart light component, a first support ring, a second support ring and a third support ring. According to the invention, students can easier Mastering the functions, layout and other knowledge of aircraft lighting system can not only train students to disassemble and assemble the components of aviation lighting system, but also train students' ability to analyze and solve problems by setting and troubleshooting.

A landing light system and steering method and computer readable medium is provided. A landing light system includes a camera, a controller, and a landing light. A tangible, non-transitory memory may have instructions for controlling a landing light. The controller may perform operations including receiving a first image at a first time from the camera, receiving a second image at a second time from the camera, estimating a focus of expansion between the first image and the second image, and aiming the landing light based on the focus of expansion.

The invention belongs to the aircraft electric control technology, and relates to the improvement of the control circuit of the aircraft landing light. It includes a right landing light control circuit and a left landing light control circuit, and is characterized in that it has a right transfer relay (15), a left transfer relay (16) and a transfer switch (17). The present invention proposes an improved aircraft landing light control circuit, which realizes the ability of the pilot on one side to control the landing light on the other side, and meets the requirements stipulated in Article 91.407 of CCAR-91-R2 "General Operation and Flight Rules". Require.