25 results about "Aircraft canopy" patented technology

A system includes a robotic arm, a rotisserie control linkage, and a computer system. The robotic arm includes a touch probe and laser head. The rotisserie control linkage is configured to couple to a transport cart. The computer system is communicatively coupled to the robotic arm and the rotisserie control linkage and is configured to control the system to probe, using the touch probe of the robotic arm, a transparent outer layer of an aircraft canopy located on the transport cart in order to determine surface measurements of the aircraft canopy. The computer system also controls the system to ablate, using a plurality of predetermined parameters and the laser head of the robotic arm, an interface layer located between the transparent outer layer and the aircraft canopy, wherein movements of the robotic arm during the ablation are based on the surface measurements.

An aircraft canopy comprises first and second canopy portions, wherein the first canopy portion includes a leading edge having a chevron shape and wherein the second canopy portion has a trailing edge complementary to the shape of the leading edge. An interconnect structure is disposed between the leading edge and the trailing edge and maintains the first and second canopy portions in assembled relationship.

The present application relates to the technical field of aviation manufacturing, in particular to a kind of gluing process of aircraft cabin transparent part edge. It includes the following steps: film is balanced at preset temperature, film is preheated before cutting;With the film after preheating, transparent part and polyester tape are bonded, and transparent part edge connecting bonding piece is obtained;Transparent part edge connecting bonding piece is cured under preset pressure, and transparent part edge connecting piece is obtained.The purpose of the gluing process of aircraft cabin transparent part edge is to solve the problems of long curing cycle and poor edge connecting bonding stability of traditional edge connecting gluing process.

Pyrotechnic devices and firing mechanisms for aircraft canopy jettison are disclosed herein. An example firing mechanism includes a housing defining a first bore, a second bore, and a channel between the first bore and the second bore, a primary charge disposed in the second bore, a closure disc between the second bore and the channel, and a firing pin assembly disposed in the first bore. The firing pin assembly includes a percussion primer and a firing pin piston including a piston body, a firing pin extending from the piston body, and a piercing pin extending from the piston body. In response to a firing signal, the firing pin piston is moved toward the primary charge such that the piercing pin punctures the closure disc and the firing pin engages the percussion primer to ignite the primary charge.

The utility model relates to an aircraft canopy lock switch which comprises a microswitch, a socket and a shell, the microswitch and the socket are both fixedly connected with the shell, the microswitch and the socket are electrically connected through a wire, and the wire is contained in the shell. By adopting the technical scheme provided by the utility model, the microswitch and the socket are jointly arranged on the surface of the shell, and the shell stably supports the microswitch and the socket and effectively protects a connecting lead between the microswitch and the socket, so that reliable electrical connection between the microswitch and the socket is kept; when the microswitch needs to be replaced or maintained, the socket is directly separated from a corresponding plug arranged in the control system, and the microswitch is taken down, so that the maintenance operation is more convenient.

This invention discloses a device and method for detecting the relative pose of two large-sized aircraft canopies. The device includes a T-shaped base with its top side face flush with the docking face of the first large-sized canopy. The top side face of the T-shape has positioning holes corresponding to the connection holes of the first large-sized canopy, allowing for positioning and connection between the aligned base and the first large-sized canopy. A suction cup support is fixedly mounted on the upper surface of the base along the docking direction, along with sliders on both sides of the suction cup support. A guide rail is slidably mounted on the upper surface of the base along the docking direction via the sliders on both sides, and a first-sized ranging sensor mounted on the upper surface of the base is located on one side of the guide rail. The body is designed as a flat plate structure. The sliding component is fixedly connected to the guide rail in the docking direction. It slides along the docking direction on the upper surface of the outer base through the guide rail and the slider. A #2 distance sensor is fixedly connected to one end face of the sliding component near the docking area. The other end is provided with a bend protruding from one side, which is used to cooperate with the #1 distance sensor to measure the sliding distance of the sliding component. The suction cup support is designed as a U-shaped structure. The bottom end face of its U-shaped structure is fixedly connected to the upper surface of the outer base. A suction cup is fixedly connected to the outer end face of each of the two side walls of its U-shaped structure. After the outer base is positioned and installed, the suction cups on both sides are used to adhere the #1 large-size cover to maintain the position of the outer base and the #1 large-size cover.

The invention discloses a mounting device and method for an omega-shaped sealing ring of an aircraft canopy control actuator cylinder, and relates to the technical field of aviation product repair, the device comprises a support, a screw and a pull claw, and a threaded hole is formed in the center of the support; the screw is connected with the threaded hole, one end of the screw is provided with a handle, the other end of the screw is rotationally connected with a check ring, and a plurality of radial notches are formed in the edge of the check ring. The pull claws are arranged around the support, one end of each pull claw is hinged to the support, and the other end of each pull claw penetrates through the corresponding notch. During installation, the omega-shaped sealing ring is installed on the non-metal expansion ring, the omega-shaped sealing ring and the non-metal expansion ring are pressed into the cover together, then the metal expansion ring is placed into the cover, the device is adopted for installation, the metal expansion ring is pressed tightly, the metal expansion ring and the cover are assembled to the outer cylinder together to be screwed and assembled, and then the piston rod is installed. The omega-shaped sealing ring can be rapidly, safely and accurately installed, it is guaranteed that the omega-shaped sealing ring is not damaged during assembly, and the sealing work performance of the canopy control actuator cylinder is guaranteed.

Pyrotechnic devices and firing mechanisms for aircraft canopy jettison are disclosed herein. An example firing mechanism includes a housing defining a first bore, a second bore, and a channel between the first bore and the second bore, a primary charge disposed in the second bore, a closure disc between the second bore and the channel, and a firing pin assembly disposed in the first bore. The firing pin assembly includes a percussion primer and a firing pin piston including a piston body, a firing pin extending from the piston body, and a piercing pin extending from the piston body. In response to a firing signal, the firing pin piston is moved toward the primary charge such that the piercing pin punctures the closure disc and the firing pin engages the percussion primer to ignite the primary charge.

The invention belongs to the technical field of aircraft thermal strength tests, and relates to a double-air-volume driving eight-energy unit control device for aircraft canopy high and low temperature tests, which comprises an air inlet, a short tee joint, a cold path valve, a thermal path valve, a long tee joint, a liquid nitrogen evaporator, an electric furnace, an oblique square tube, a rectification section, a partition plate, a test section, an airflow regulating valve, an air return opening and a control system. The two paths of air inlets are in butt joint with two sets of fan air outlets correspondingly, and a double-air-volume driving structure is formed. Each path of air inlet is divided into an upper-layer hot path and a lower-layer cold path through a short tee joint, the hot path is controlled to be opened and closed through a hot path valve, and the cold path is controlled to be opened and closed through a cold path valve; each group of hot circuit and cold circuit is divided into two groups of branches through a long tee joint, the hot circuit branches are provided with electric furnaces, the cold circuit branches are provided with liquid nitrogen evaporators, four groups of electric furnaces and four groups of liquid nitrogen evaporators are formed, and eight energy units are formed; synchronous combined control over the spanwise temperature and the course temperature of the circulating airflow is achieved, then the spanwise temperature field uniformity and the course temperature gradient of the canopy are accurately adjusted, and the ground test condition is closer to the actual flight condition.

The application discloses a large-curvature aircraft canopy cover transparent piece damage inlay type additive repair method and structure, relates to a kind of quick repair method of aircraft canopy cover damage, specifically includes the following steps: removing damaged area on organic glass canopy cover, and polishing hole, hole is polished into inlay type groove inward;Flexible inner baffle is pasted on the inside of organic glass canopy cover and shields hole, and repair filler is filled in hole, flexible outer baffle is pasted on the outside of organic glass canopy cover and shields hole;The hole area filled with repair filler is heated, after heating, cooling, so that repair filler is cooled and solidified into shape.Large-curvature aircraft canopy cover transparent piece damage inlay type additive repair structure is repaired and formed using a kind of large-curvature aircraft canopy cover transparent piece damage inlay type additive repair method.The application solves the problems of repair adaptability of large-curvature canopy cover complex damage shape, limited view after repair canopy cover and local strength reduction.

The utility model discloses a locking device for a light aircraft canopy, and relates to the field of aircraft cabins. The device comprises a fixed lock seat, a dynamic lock seat and a pull rope; a guide block is fixedly connected to the top of the fixed lock seat, a lock pull rod is slidably connected to the guide block, and the rear end of the pin shaft rod is fixedly connected to the pull rope; a rocker arm is arranged on one side of the lock pull rod, a guide sliding hole is arranged on the rocker arm, a pin shaft rod is arranged in the guide sliding hole, the pin shaft rod is fixedly connected to the lock pull rod, the lower end of the rocker arm is fixedly connected to the rotating shaft, the rotating shaft is rotatably connected to the shaft seat, the shaft seat is fixedly installed on the fixed lock seat, and an inner handle is arranged at one end of the rotating shaft; the dynamic lock seat is located above the fixed lock seat, a lock sleeve is arranged at the bottom of the dynamic lock seat, and the lock sleeve is plugged and matched with the lock pull rod. The utility model adopts a latch form, has a simple and reliable structure, adopts an emergency pull rope to realize the opening outside the cabin, does not affect the aesthetics of the cabin, and can also reduce the influence of the protruding objects of the aircraft fuselage on the aerodynamic performance of the aircraft.

The invention relates to the technical field of maintenance of canopy with different shapes, in particular to a multifunctional aircraft canopy maintenance platform which comprises a structure for supporting the maintenance platform and a platform base for realizing automatic lifting of the platform, and further comprises a front moving table, a platform frame body and a moving pressing mechanism, according to the invention, the parking, the length size and the opening size of the canopy in different shapes can be adjusted and controlled during maintenance; and when the canopy in different shapes is repaired, the height can be adjusted through the hydraulic driver, the requirement for portable maintenance of the canopy in different shapes is met, the man-machine effect is improved, the universality is high, economical and practical effects are achieved, operation is convenient, and the structure is stable and reliable.

The utility model discloses an aircraft canopy transfer trailer, and belongs to the technical field of aeronautical manufacturing and maintenance, the aircraft canopy transfer trailer comprises a frame, the frame is rotatably connected with a fixing part through a first rotating seat, the frame is rotatably connected with a bearing part through a second rotating seat, and the bottom of the fixing part and the bottom of the bearing part are both fixedly connected with clamping blocks; a bearing plate I is fixedly mounted in the frame, and a bearing plate II is fixedly mounted at the rear end of the frame; by arranging the first rotating seat and the second rotating seat, the vehicle frame is rotationally connected with the fixing component and the bearing component, the fixing component and the bearing component can be folded and stored in the vehicle frame when not in use, and therefore space can be saved, storage and long-distance transportation are facilitated, and the cost of transition transportation is reduced; and through linkage matching between the limiting units and the clamping blocks, the fixing component and the bearing component can be conveniently limited and fixed, and the stability of the fixing component and the bearing component during working is ensured.

The invention belongs to the technical field of design of aircraft canopy supporting rod fastening structures, and particularly relates to an aircraft canopy supporting rod fastening structure and a fastening method thereof.The aircraft canopy supporting rod fastening structure comprises a force bearing block, a bolt and a nut; the bearing block is hinged to one end of the supporting rod; the other end of the supporting rod is hinged to the cabin cover, the cabin cover is installed on the cabin force bearing frame, and a strip-shaped installation hole is formed in the cabin force bearing frame. The bolt penetrates through the strip-shaped through hole, and the head is rectangular; anti-rotation grooves are formed in the top ends of the bolts; the nut is screwed on the bolt; the nut is a butterfly nut; the rectangular heads of the adjusting bolts are parallel to the strip-shaped mounting holes in the cockpit force bearing frame and can penetrate through the strip-shaped mounting holes, the rectangular heads of the adjusting bolts are perpendicular to the strip-shaped mounting holes in the cockpit force bearing frame, the nuts are tightened, the force bearing block can be fastened to the cockpit force bearing frame, and therefore the supporting rods are fastened, and the cockpit cover is supported at the opening position.

The invention provides a high-resolution image detection device with a magnetic attraction function, and relates to the technical field of image detection devices. The device comprises a cover plate assembly, wherein the cover plate assembly is magnetically attracted on a main body measurement module; the camera is mounted in the cover plate assembly and is arranged corresponding to an aircraft hatch cover lock; and the data conversion plate is arranged in the cover plate assembly and is electrically connected with the camera and the main body measurement module respectively. On the whole, the device is high in integration level, small in occupied space and capable of achieving detection in a narrow space range.

The invention belongs to the technical field of aircraft canopy glass heating and shaping, and discloses an aircraft canopy glass clamping and shaping device and a using method thereof. Comprising an integral frame and T-shaped clamps, the overall frame is similar to a canopy framework in shape and comprises a front arc baffle, a rear arc baffle and two side baffles. The inclination angles and radians of the front arc baffle and the rear arc baffle are consistent with those of the canopy framework; the T-shaped clamp is a clamping fixture and is installed on the overall frame in a threaded connection mode. The T-shaped clamp comprises a stress application rod, a screw rod, a top plate, a support arm, a bottom plate, a positioning pin shaft, a bolt, a tongue piece, a baffle ring, a nut and a baffle plate; according to the invention, large appearance difference before and after shaping of the glass is prevented, and size deviation is extremely easy to generate when allowance cutting work is carried out before shaping of the glass. And non-metal parts on the canopy framework are prevented from aging. The structure is simple and operation is convenient.

Due to the recent rise in temperatures, heat countermeasures for drone control equipment are becoming necessary. We provide a canopy for aircraft with a heat dissipation structure that prevents the temperature inside the canopy from becoming too high. [Solution] The upper part of the canopy is made of corrugated sheets and heat dissipation fins, and the temperature inside the canopy is lowered by leaving a small space and installing a radiation heat shield.

The invention discloses an aircraft canopy optical distortion correction method based on a generative adversarial network, and the method comprises the steps: 1, collecting a distorted image with aircraft canopy glass and a non-distorted image without aircraft canopy glass, and taking the collected distorted image and non-distorted image as training samples; 2, constructing a generative adversarial network comprising a generator and a discriminator, designing a loss function, dividing a training sample into a training set and a test set, and training and testing the generative adversarial network by using the training set and the test set to obtain a distortion correction network; and step 3, inputting the collected distorted image into a distortion correction network, and correcting the distorted image by using the distortion correction network to obtain a non-distorted image. The method for correcting the optical distortion of the aircraft canopy has stronger image recovery capability and detail retention capability in the aspect of correcting the image distortion caused by the aircraft canopy, and is suitable for high-precision image processing requirements in a complex environment.

The invention belongs to the technical field of aircraft canopy heat intensity test equipment, and relates to an aircraft canopy test bed fairing line and angular displacement linkage strong protection switch device which comprises a universal cabin, a canopy test piece, a fairing and a fairing switch device. The fairing is buckled on the table top of the general cabin and located above the canopy test piece, and the fairing switch device and the general cabin are arranged in parallel; according to the invention, through linkage of linear displacement and angular displacement, a full-open type opening space is realized, strong protection functions of overturning prevention and collision prevention are realized, and the problems of limited opening space and easy damage of a test piece in the prior art are solved.

This invention relates to the field of electromagnetic shielding technology, and more specifically, to an electromagnetic shielding glass for aircraft cockpit canopies and its preparation method. The glass comprises a transparent substrate made of hyperboloid methyl methacrylate (MMA) acrylic glass with a thickness of 10-20 mm and a basic light transmittance ≥91%. The inner surface of the transparent substrate has grooves with a grid structure etched by laser. Metal paste is filled into the grooves by ultrasonic filling, and the metal paste is sintered and cured to form a metal grid. Anti-reflective and anti-reflective coatings are provided on both sides of the transparent substrate and on the outer side of the metal grid. Compared with traditional transparent conductive oxide thin film materials, this invention significantly improves transmittance and strong electromagnetic wave shielding effectiveness, and has better environmental adaptability.

A canopy fragilization system for use in an aircraft ejection system to break a canopy (24, figure 1) of an aircraft (10, figure 1) comprising a base 210 configured to pivotally couple to an ejection

This utility model relates to the field of aircraft repair, specifically disclosing an aircraft cockpit canopy system refueling and venting inspection device. The device includes a housing, with multiple connectors for pipe installation installed on the lower side wall of one side wall. The two ends of each connector are located inside and outside the housing, respectively. A transparent observation tube is connected to the end of the connector inside the housing, and the observation tube is open at both ends. This application enables effective evaluation of the cleaning, refueling, and venting effects of the aircraft cockpit canopy system, avoiding the misjudgment problems associated with traditional direct visual inspection methods. The observation tube, made of highly transparent borosilicate glass, allows for effective observation of whether air bubbles are present in the oil. The device has a simple overall structure, is easy to use, requires no maintenance in daily use, and meets the needs of both indoor and outdoor use under complex environmental conditions.

The utility model discloses an angle mounting device for a control actuator cylinder of an aircraft canopy, which relates to the technical field of aviation product maintenance and comprises a working platform truck. A working platform of the working platform vehicle is provided with a double-seat angle mounting module and a single-seat angle mounting module, and the double-seat angle mounting module and the single-seat angle mounting module are arranged on the two sides of the working platform respectively; each of the double-seat angle mounting module and the single-seat angle mounting module comprises a bracket fixed on the working platform, the brackets are used for supporting a canopy control actuator cylinder to be mounted, the double-seat angle mounting module and the single-seat angle mounting module further comprise lock pin positioning pieces mounted on the working platform, and the lock pin positioning pieces are arranged on the outer sides of the brackets; and the lock pin positioning piece is connected and positioned with a joint on the canopy control actuating cylinder. The mounting device provided by the utility model is stable in mounting angle and accurate and adjustable in mounting point positioning, has compatibility of mounting of different machine types, and can effectively improve the production efficiency and solve the potential safety hazard of production.

1. The name of the design product: awning support rod. 2. The use of the design product: for supporting awning or tent and other outdoor products. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1.

The application belongs to the technical field of airplane debugging process, and particularly relates to a process method and a special test bench for an airplane canopy cover air tightness and strength test, comprising an oil tank, a manual pump, a reversing valve, a process actuating cylinder and a controller. The reversing valve is a three-position four-way reversing valve. Two oil ports on one side of the reversing valve are connected with the manual pump and the oil tank, and two oil ports on the other side of the reversing valve are connected with the inlet and outlet oil ports of the process actuating cylinder through hydraulic rubber pipes. The oil tank and the manual pump are connected with each other. The manual pump and the reversing valve are provided with sensors, and the sensors are electrically connected with the controller. The assembly process of the canopy cover pneumatic hydraulic system is successfully moved to the final assembly stage, and the process cross and repeated disassembly in the assembly and final assembly stages are completely avoided. The air tightness and strength test in the assembly stage can be independently and advancedly carried out, and the overall production cycle of the airplane is greatly compressed.