29 results about "Landing lights" patented technology

The invention relates to the technical field of bus control, in particular to a method and system for controlling and monitoring landing light based on a CAN bus. The method comprises the following steps: setting a light control node in an aircraft landing light system, and performing control network connection and landing light local response control on the light control node and a central control unit by using a CAN bus protocol to generate a landing light local response control instruction; starting corresponding landing light in an aircraft landing light system according to the landing light local response control instruction, performing light condition real-time monitoring and judgment analysis, and if the landing light is determined to be in an on-light state, performing brightness non-uniformity control management so as to execute on-state brightness non-uniformity control work; and if it is determined that the landing light working state is a closed state, light operation fault control management is carried out to execute closed state fault adjustment control work. The intelligent level of the landing light control system can be improved.

The invention relates to the technical field of lighting devices, and discloses a landing lamp which comprises a mounting frame, a lamp body, a rotating ring, a first driving mechanism and a second driving mechanism, the rotating ring is arranged at one end of the mounting frame and can rotate around the Z axis, and the two sides of the lamp body are hinged to the rotating ring; the first driving mechanism is connected with the rear side of the lamp body and the other end of the mounting frame, and is used for driving the lamp body to rotate around a hinge point of the lamp body along a Y axis so as to realize pitch angle adjustment of the lamp body; the second driving mechanism is connected with the rotating ring and the other end of the mounting frame and used for driving the rotating ring to rotate around the Z axis so as to drive the lamp body to achieve adjustment of the roll angle. Adjustment can be automatically carried out according to the pitch angle or the deflection angle of an airplane, the lamp body is always located at the optimal pitch angle and the optimal deflection angle, it can be guaranteed that the landing lamp meets the efficient illumination requirement in the two landing states at the same time, lamp beads do not need to be added, cost is reduced, and the performance of the landing lamp is guaranteed.

The present invention relates to the field of image processing technology, and in particular to an image data processing system for diagnosing faults in landing lights of unmanned aerial vehicles. The system uses the brightness value under a fixed gear to statistically calculate the first suspected fault area in the light-emitting element area, analyzes the brightness changes caused by different gear changes at different heights, and further screens out the second suspected fault area through the distribution of the brightness change amplitude. Analyze the correlation of the brightness change amplitudes of areas at different positions in the second suspected fault area, and further correct the fault credibility in combination with the distance between the unmanned aerial vehicle and the landing light image acquisition device at each height. Determine the final fault probability and accurately locate the fault. The present invention effectively analyzes each light-emitting element area based on factors such as brightness changes, the influence of adjacent array brightness, and the distance between the image acquisition device and the landing light to obtain an accurate final fault probability and effectively locate the fault.

The invention provides a ducted power vertical take-off and landing light motion eVTOL which is composed of a fuselage, a fixed wing assembly, a ducted fan power system, an energy system, a flight control system and an undercarriage, and higher-precision and flexible attitude control can be achieved through cooperative control of a small number of ducted fans and wing surfaces. The defects that in the prior art, the structure is complex, control precision and safety are poor, light weight is insufficient, energy consumption is high and the like are overcome, and the use requirements of low-altitude motion scenes can be better met. According to the eVTOL, a skating or vertical take-off and landing mode can be flexibly selected according to actual road conditions, the requirement for a special runway is reduced, and the eVTOL has obvious advantages in the aspects of operation convenience, energy consumption and safety redundancy.

The invention discloses an aircraft landing lamp. The aircraft landing lamp comprises a light source part and a driving part. The light source part is provided with a light source shell and a light source plate in the light source shell, and the driving part is provided with a driving shell, a driving plate and an axial flow fan, wherein the driving plate and the axial flow fan are arranged in the driving shell. The aircraft landing lamp has the beneficial effects that airflow generated by the axial flow fan is exhausted from inside to outside along the cooling fins, that is, heat is rapidly dissipated in a forced air cooling mode, heat conduction and convection of the aircraft landing lamp are guaranteed, rapid and effective heat dissipation is achieved, and temperature control is guaranteed while the weight reduction requirement is met.

The present invention relates to the technical field of bus control, and in particular to a method and system for controlling and monitoring landing lights based on the CAN bus. The method includes the following steps: establishing a lighting control node in the aircraft landing lighting system and using the CAN bus protocol to control the network connection between the lighting control node and the central control unit and perform local response control of the landing lights, generating a local response control instruction for the landing lights; starting the corresponding landing lights in the aircraft landing lighting system according to the local response control instruction for the landing lights and performing real-time monitoring and judgment analysis of the lighting conditions. If it is determined that the working state of the landing lights is the on state, uneven brightness control management is performed to execute the uneven brightness control work in the on state; if it is determined that the working state of the landing lights is the off state, lighting operation fault control management is performed to execute the fault adjustment control work in the off state. The present invention can improve the intelligent level of the landing lighting control system.

The application provides a novel approach to landing light system, including: landing light, including static landing light and dynamic landing light, used to guide the aircraft to land on the deck at night or in the case of insufficient lighting; main drive box, including drive detection board and communication board, used to detect the state information of the landing light and to pack and transmit the obtained information to the landing light control cabinet; landing light control cabinet, including landing light control device, used to realize the control of the landing light, including power on / off operation, dimming, state monitoring and fault alarm; the landing light is connected with the main drive box through a junction box; the main drive box is connected with the landing light control cabinet through the communication board and the power line; the landing light control cabinet is connected with two working circuits. The application makes the use and maintenance of the light more convenient, and more beautiful.

Systems and methods for deicing an aircraft landing light may include a metal mesh conductor coupled to a lens of a landing light. The systems and methods may include a power supply, a temperature sensor, a deicing control unit, an aircraft light having a lens, and a mesh coupled to the lens. The temperature sensor may be a microwave resonator sensor configured to sense the temperature of the landing light and send signals to the deicing control unit. The signals may be configured to instruct the deicing control unit to either apply an electric current to the mesh, or cease applying an electric current to the mesh, depending on the landing light temperatures. The deicing control unit may receive landing pulses from a flight control system. The pulses may indicate that the aircraft is landing or has landed.

The utility model discloses a controllable arrival lamp for an elevator, which comprises a mounting plate, a station lamp holder and a mounting piece with an indicator lamp, a butt joint assembly is arranged on the outer side of the station lamp holder, a linkage gear set is arranged in a mounting strip, the gear set is respectively connected with a supporting shaft and a connecting pipe with a limiting strip, and a liftable column body and a reset spring are arranged in the connecting pipe. The control column is driven by the rotary knob to drive the gear set to be in linkage so that the positioning pin can be inserted into the locking hole, and installation can be completed by rotating 180 degrees. And the protection assembly adopts an acrylic cover in threaded connection, so that the replacement is convenient. Rapid installation is achieved through gear linkage, automatic locking is guaranteed through a spring reset mechanism, maintenance is convenient through threaded connection of the cover body, the advantages of being high in installation efficiency, reliable in connection, convenient and fast to maintain and the like are achieved, and the problems that a traditional arrival lamp is complex in installation and prone to loosening are effectively solved.

The utility model belongs to the technical field of aircraft assembly and connection, and relates to a device for mounting a landing lamp socket frame on a nacelle of a main landing gear and scribing skin allowance. The utility model particularly relates to a landing lamp mouth frame positioning and line drawing device. Comprising a support, a connecting plate and a positioning scribing disc. The connecting plate comprises a vertical plate and a transverse plate, the vertical plate and the transverse plate are connected through a fork lug and a threaded connecting pin, the support is of an L-shaped structure and is connected with the vertical plate of the connecting plate through a connecting bolt, a positioning hole is formed in the transverse plate, and the positioning scribing disc is connected with the transverse plate through the positioning hole by adopting a screw. By using the landing lamp socket frame positioning and line drawing device, the installation difficulty of landing lamp socket frame parts is reduced, the installation precision is high, the operation is simple, the use is convenient, the installation efficiency is high, and meanwhile, the position precision and the roundness precision of landing lamp socket frame skin trepanning are improved; the problems that the installation angle of the landing lamp deviates and the gap between the landing lamp and the periphery of the opening frame skin is not uniform are solved.

The invention discloses a retractable aircraft landing lamp with a retractable synchronization function and a retractable method. The retractable aircraft landing lamp comprises a landing lamp shell, a landing lamp holder and an actuating device used for retracting and releasing the landing lamp holder, and a lamp holder driving printed board used for controlling the landing lamp holder to illuminate and an actuating control printed board used for controlling the actuating device to retract and release are contained in the landing lamp shell. An electric connector is fixed to the landing lamp shell. The landing lamp has the beneficial effects that the landing lamp is small in size and light in weight, the master lamp and the slave lamp can be interchanged, the landing lamp can stay at any position, and the folding and unfolding consistency of the two lamps is good.

The application relates to the technical field of lighting devices, and discloses a landing light, which comprises a mounting frame, a lamp body, a rotating ring, a first driving mechanism and a second driving mechanism. The rotating ring is rotatably arranged at one end of the mounting frame around the Z axis. The two sides of the lamp body are hingedly connected with the rotating ring. The rear side of the lamp body and the other end of the mounting frame are connected with the first driving mechanism, which is used for driving the lamp body to rotate around the hinged point along the Y axis, so that the pitch angle of the lamp body is adjusted. The other end of the mounting frame and the rotating ring are connected with the second driving mechanism, which is used for driving the rotating ring to rotate around the Z axis, so that the lamp body is driven to adjust the roll angle. The application can automatically adjust according to the pitch angle or the deflection angle of an airplane, the lamp body is always at the optimal pitch angle and the optimal deflection angle, the landing light can meet the high-efficiency lighting requirements in two landing states, the lamp beads do not need to be increased, the cost is reduced, and the performance of the landing light is ensured.

The invention provides a retractable landing lamp and a manufacturing process thereof, and relates to the technical field of landing lamps, and the retractable landing lamp comprises an LED light source, a rotary support, a gear assembly, a driving assembly, a pin shaft and a housing. The gear assembly comprises a power mechanism and a multi-stage speed reduction mechanism which are arranged in the first shell, and the driving assembly comprises a driving circuit arranged in the second shell. The first shell and the second shell are detachably connected and jointly define a rotating space, the pin shaft penetrates through the two shells and the rotary support to enable the pin shaft to be rotatably supported in the space, and a final-stage output gear of the multi-stage speed reduction mechanism is meshed with a tooth-shaped structure on the arc-shaped outer edge of the rotary support. The rotary support is driven by the multi-stage transmission mechanism to rotate around the pin shaft, electric adjustment of the LED light source in the range of 0-90 degrees in the vertical direction and hovering at any angle are achieved, the technical problem that the irradiation direction of a traditional fixed landing lamp cannot be adjusted is effectively solved, and the illumination adaptability and safety of an airplane under different take-off and landing conditions are remarkably improved.

The utility model relates to a protective handrail base, belongs to the technical field of building construction, and particularly relates to a non-landing light well edge protective handrail base which comprises a well turnup, and four lower steel plates are attached to the top of the well turnup. Adjusting clamping grooves in the upper steel plate and the lower steel plate are overlapped and then fixed through bolts, elastic anti-skid rubber on the lower steel plate is attached to an upturning wall body, a rotating block is rotated to drive a threaded column to rotate, an extrusion block is driven to fix the wall face of the light well, and a steel pipe threaded sleeve is in threaded connection with a steel pipe stand column guardrail. The light well is protected and warned, meanwhile, the light well is convenient to mount and dismount, the use efficiency is improved, and the problems that when an existing light well is protected, conventional edge protection rails are mostly adopted to be directly placed on a roof, different light wells are not convenient to protect and mount, protection materials are wasted, and the service life of the light well is prolonged are solved. And meanwhile, the personal safety of workers cannot be guaranteed during disassembly.

An auxiliary landing system for an aircraft having a landing light system with landing lights capable of emitting landing light beams, the auxiliary landing system being in communication with the landing light system and comprising: an image collecting device configured to collect information about a landing runway; a control device configured to control the rotation of the landing lights based on the information from the image collecting device to direct the landing light beams toward a centerline of the landing runway; and a processing device configured to obtain auxiliary landing information based on rotation information of the landing lights provided by the landing light system and provide the auxiliary landing information to a display device on the aircraft to assist a pilot in landing the aircraft. The auxiliary landing system of the present invention obtains auxiliary landing information by the image collecting device in cooperation with the landing light system to assist the pilot in landing. The present invention also provides an aircraft comprising the aforementioned auxiliary landing system and an auxiliary landing method for an aircraft.

The utility model provides a movable landing light comprehensive test bench, which comprises a test bench, a tester is fixed at one end of the top of the test bench, an operation panel is arranged on the surface of the front end of the tester, a clamping assembly is arranged on the surface of the middle of the test bench, and the clamping assembly comprises a sliding frame. Two moving blocks are symmetrically and slidably connected to the interior of the sliding frame, a rotating seat is fixed to the top of each moving block, vertical plates are rotatably installed on the inner side of each rotating seat, a plurality of clamping plates are arranged at the tops of the two vertical plates, the adjacent clamping plates are rotatably connected through rotating shafts, and two sliding rails are fixed to the positions, corresponding to the sliding frame, of the top of the test bed; compared with the prior art, the stability can be improved by adopting a landing lamp tightly-attached clamping mode through the clamping assembly, the landing lamp can be driven to horizontally move and rotate for angle and telescopic testing, the limiting assembly is used for bunching and limiting a connecting line of the tester and the landing lamp, and the disorder of the detection table top is prevented.

The invention relates to the technical field of image processing, in particular to an image data processing system for unmanned aerial vehicle landing lamp fault diagnosis. According to the system, a first suspected fault area in a light emitting element area is counted by using a brightness value under a fixed gear, brightness changes generated by changes of different gears are analyzed at different heights, and a second suspected fault area is further screened out through distribution of brightness change amplitudes. And analyzing the relevance of the brightness variation amplitudes of different position areas in the second suspected fault area, and further correcting the fault credibility in combination with the distance between the unmanned aerial vehicle and the landing lamp image acquisition equipment at each height. And determining a final fault probability and carrying out accurate fault positioning. According to the invention, each light-emitting element area is effectively analyzed based on factors such as brightness change, adjacent array brightness influence, distance between the image acquisition equipment and the landing lamp and the like, so that an accurate final fault probability is obtained and effective fault positioning is carried out.

The invention provides an aircraft landing lamp condensation point adjusting method, and belongs to the technical field of aircraft landing lamp debugging, and the method specifically comprises the following steps: installing a laser pen on a landing lamp, and enabling the light of the laser pen to coincide with the optical axis of the landing lamp; a vertical circular target plate is placed at the position away from the aircraft nose by a preset distance Dt, and ideal intersection point coordinates of ideal optical axes of the landing lamps and the target plate are calculated; calculating a light spot constraint range of the laser pen on the target plate based on the ideal intersection point coordinates and an allowable error range; and the angles of all landing lamps on the airplane are adjusted to enable the light spots of the laser pen to fall within the constraint range. By means of the processing scheme, the landing lamp adjusting efficiency and accuracy are high.

The invention provides a PAR64 landing lamp with a full LED light source, which relates to the technical field of aviation lighting and comprises a metal main body shell matched with a standard PAR64 interface, a front cover assembly in sealed connection, an optical assembly on the inner side, an integrated driving assembly in a cavity and a bottom binding post. According to the integrated driving assembly, an LED chip and a driving circuit are integrated on the same printed circuit board, and the integrated driving assembly is tightly connected with the inner wall of the shell through a thermal phase change heat conduction pad. The lens adopts a total internal transmission reflection lens; the radiating fins are non-uniformly distributed, and the position density corresponding to the driving assembly is maximum; the driving circuit is AC-DC dual-purpose and the power supply input is not divided into positive and negative poles; the glass screen is made of a quartz material; the shell is provided with a waterproof ventilation valve. The invention further discloses a manufacturing process of the landing lamp. The LED landing lamp has the advantages of being high in integration, efficient in heat dissipation and convenient and fast to maintain, a traditional PAR64 landing lamp can be directly replaced, reliability is remarkably improved, and the service life is remarkably prolonged.

The utility model provides a combined lens type aircraft landing lamp, which relates to the technical field of landing lamps, and comprises a main body shell, the top of the main body shell is provided with a placing groove, the side surface of the placing groove is provided with a supporting part, the supporting part is detachably connected with a lens mounting plate, the lens mounting plate is provided with a first mounting groove and a second mounting groove, and the first mounting groove and the second mounting groove are arranged in the main body shell. Different lenses are installed in the first installation groove and the second installation groove respectively, the outer side of the lens installation plate is connected with a front screen assembly, LED assemblies are arranged at the corresponding positions of the bottoms of the first installation groove and the second installation groove, and the top of the lens installation plate is connected with a lens pressing plate. The LED aircraft landing lamp is used for solving the technical problems that the requirements for effective scattering angles of existing LED aircraft landing lamps are different, the requirements for angles of different airplanes are different, and customized lens molds are high in cost, long in machining period and poor in economical efficiency.

A laser landing assisting system of a vertical take-off and landing aircraft comprises a machine shell, a laser dot matrix module, a laser ranging module and a control module. The machine shell comprises an upper cover plate and a bottom cover. The upper cover plate is made of a high-transmittance high-hardness tempered glass plate / acrylic plate and a metal frame. A laser dot matrix module, a laser ranging module and a built-in rechargeable battery are mounted in the bottom cover; suckers, magnets, permanent mounting holes, quick-release mounting holes and the like can be mounted at the bottom of the bottom cover. The high-contrast and high-brightness laser dot matrix module is used for emitting optical signals, colors, patterns (two-dimensional codes), symbols and the like can be changed, high-contrast and high-definition guidance and data information of a ground laser range finder and an air traffic control system are provided for an airborne camera, and the problems that an existing GPS / Beidou navigation system is prone to being interfered, and the navigation efficiency is high can be effectively solved. The problems that the recognition rate of an airborne camera and a matched landing lighting system is low in severe weather, and communication between an aircraft and a take-off and landing field is not smooth are solved, and the safety and reliability of a landing assisting system are improved.

A lighting pod for an aircraft, such as a helicopter. The lighting pod includes aerodynamic housing in which multiple lights are mounted in optimum positions providing efficient lighting and lesser air drag. The lighting pod includes taxi lights, landing lights, scene lights, rear lights, hover lights, hoist lights, and headlights. The lighting pod having all the essential lights can be easily installed and removed from an aircraft.

A lighting pod for an aircraft, such as a helicopter. The lighting pod includes aerodynamic housing in which multiple lights are mounted in optimum positions providing efficient lighting and lesser air drag. The lighting pod includes taxi lights, landing lights, scene lights, rear lights, hover lights, hoist lights, and headlights. The lighting pod having all the essential lights can be easily installed and removed from an aircraft.

1. The name of the design product: airplane take-off and landing light. 2. The use of the design product: for airplane take-off and landing light. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: front view.

The application discloses an aviation landing light retraction and deployment adjusting driving device and application, which is used for controlling aviation landing light retraction and deployment. The aviation landing light retraction and deployment adjusting driving device is composed of a device shell, a two-stage worm and gear pair, a driving motor, a gear assembly, a rack assembly and an angular displacement sensor and the like. The aviation landing light retraction and deployment adjusting driving device has the advantages that the structure is compact and reasonable, the space requirement is small, the work is reliable, and the aviation landing light retraction and deployment adjusting function can be realized in a small space volume.

The utility model relates to the field of landing lamp test equipment, in particular to a simulation dynamic wind load test platform for a landing lamp, which comprises a working platform and a dynamic distortion rotating speed sensor, and is characterized in that a magnetic powder loader is fixedly arranged on the working platform; a transmission shaft is arranged on the magnetic powder loader; a rotating shaft is arranged on the dynamic distortion rotating speed sensor, one end, far away from the magnetic powder loader, of the transmission shaft is connected with one end of the rotating shaft through a rigid coupling, and the other end of the rotating shaft is connected with a landing lamp testing device; according to the crankshaft type lamp holder pressing plate, the lamp holder pressing plate and the surface of a tested lamp can be kept in a parallel pressing state all the time, the connecting lugs are correspondingly arranged on the two sides of the pressing plate body, the connecting shafts are arranged on the connecting lugs respectively, the connecting shafts are aligned with the rotating center of the lamp, and therefore it is guaranteed that the load borne by the lamp face, namely the windward face is a constant value all the time; and the error is minimum.

The utility model provides an elevator arrival lamp bottom box structure which comprises a reserved installation assembly and an elevator control structure, a limiting locking mechanism is installed on the top of the reserved installation assembly, a supporting base plate assembly is arranged on the inner wall of the reserved installation assembly in a sliding mode, and guide assemblies are arranged at the side ends of the supporting base plate assembly and the reserved installation assembly. An elastic guide assembly is arranged on the inner wall of the supporting base plate assembly. According to the elevator arrival lamp bottom box structure, the supporting base plate assembly and the elastic guide assembly are arranged between the inner walls of the structure and used in cooperation, three-dimensional protection treatment can be conducted on a main body of an internal structure, pressing force is dispersed to an equipment overall frame through a base plate, and shell cracking caused by too large local stress is avoided; and the arranged elastic guide assembly can accurately guide the pressing force of the user, and the structure can automatically rebound, so that excessive pressing operation of the user is reduced.

The utility model relates to the technical field of helicopter safe flight equipment discloses an improved helicopter bird repelling lamp device, including stroboscopic landing light, the front end of the stroboscopic landing light outer surface is embedded with LED, the upper end of one side of the stroboscopic landing light outer surface is embedded with control box, the rear end of one side of the stroboscopic landing light outer surface is embedded with four binding posts, the lower end of one side of the stroboscopic landing light outer surface is embedded with stroboscopic relay, the upper end of the stroboscopic landing light is fixed with mounting bracket, the inside of control box is provided with 28V landing light input signal, ground signal, 28V stroboscopic input signal and landing light control signal, in the utility model, after setting up pulse control box on landing light, the pulse control box can control and adjust landing light, so that the function of one lamp with multiple uses can be realized, and the effect that landing light is also bird repelling lamp is reached.

A multifunctional wingtip light for aircraft, integrating a taxi light, a navigation chip-on-board (COB) light module, a strobe COB light module, a landing light module, and an optional ground illumination module within an aerodynamically optimized housing. The configuration enhances aircraft visibility, operational safety, and retrofit compatibility while reducing drag and improving energy efficiency.