5 results about "Aircraft canopy" patented technology

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 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.

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 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.