A kind of integral forging method of aircraft two-seat canopy frame
A technology of integral forging and canopy, applied in the direction of metal processing equipment, etc., can solve the problems of cracks on the edge of the hole of the transparent glass part of the canopy, poor rigidity of the frame of the canopy forged in sections, poor assembly coordination and interchangeability, etc., and achieve improvement The effect of comprehensive performance and service life, reducing the number of structural parts, and complete streamlines
Active Publication Date: 2016-05-11
JIANGXI HONGDU AVIATION IND GRP
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[0003] The purpose of the present invention is to realize the overall forging of the double-seat canopy frame of an aircraft, and solve the performance limitations of the segmented forged canopy frame, such as poor rigidity, easy deformation, poor assembly coordination and interchangeability, and easy cracks on the hole edge of the transparent glass part of the canopy. sex
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[0012] Attached below figure 1 , 2 The present invention is described in detail:
[0013] A method for integrally forging a two-seat canopy frame of an aircraft, comprising the following method steps:
[0014] A) To prepare bar stock of LD5 material, heat it in an electric furnace at 430°C-450°C, keep it warm for 9h-15h, and free forge it to the specified size on a 5,000-ton hydraulic press after it comes out of the furnace. After the billet is air-cooled, press figure 1 The shape of the medium blank is processed by the inner hole and the shape of the blank, and then the blank is heated in an electric furnace at 430°C to 450°C and kept for 6h to 12h. After being released from the furnace, it is integrally forged on a 10,000-ton hydraulic press. Solution treatment, the temperature is 509 ℃ ~ 515 ℃, heat preservation 2h ~ 2.5h, the quenching water temperature is controlled at 70 ℃ ~ 80 ℃ after the furnace is released to reduce the quenching deformation of the forging, and then...
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The invention relates to an airplane two-seater canopy framework integral-forging method and belongs to the technical field of the hot working technology. The airplane two-seater canopy framework integral-forging method includes preparing rods made of LD5 materials, heating to the temperature of 430-450 DEG C by an electric furnace, keeping the temperature for 9-15 hours, performing open-die forging to the rods on a 5000-ton hydraulic press until reaching the specified dimension requirements after sending the rods out of the electric furnace, processing inner bores and profiles of blanks after cooling the blanks in air, heating the blanks to the temperature of 430-450 DEG C by the electric furnace, keeping the temperature for 6-12 hours, performing integral forging to the blanks on a 10000-ton hydraulic press to complete the shaping process after sending the blanks out of the electric furnace, checking dimensions according to the integral template, performing solution treatment to the blanks in the electric furnace at the temperature of 509-515 DEG C after the dimensions are checked to be qualified, keeping the temperature for 2-2.5 hours, quenching the blanks being sent out of the electric furnace while controlling the water temperature to be 70-80 DEG C so as to reduce quenching distortion, performing dimension correction on the 5000-ton hydraulic press until reaching the designed dimension requirements, and then ageing in the electric furnace at the temperature of 514-520 DEG C, and keeping the temperature for 8-15 hours. The time interval between the quenching and the ageing is smaller than 6 hours.
Description
technical field [0001] The invention relates to an integral forging method for an aircraft double-seat canopy skeleton, and belongs to the technical field of thermal processing. Background technique [0002] There is no precedent for integral forging of two-seat canopy frames for aircraft at home and abroad, and the canopy frames of various types of aircraft in China are composite structures composed of multiple parts. The canopy frame of the T50 aircraft jointly developed by South Korea and the United States is an all-composite structure, while the canopy frames of other foreign aircraft are mostly combined and rear-opening structures. In the past, the canopy skeleton for two-seat aircraft was forged by forging the front arc frame, the middle arc frame, and the rear arc frame separately, and the canopy skeleton was formed by combining the three arc frames and the profiles on both sides. The frame of the canopy that is forged in sections has poor rigidity, poor stability, a...
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IPC IPC(8): B21J5/00
Inventor 傅永平万里鹏胡建冬胡建英
Owner JIANGXI HONGDU AVIATION IND GRP