Aircraft telescopic landing gear capable of controlling length

Abstract

The invention discloses an aircraft telescopic landing gear capable of controlling the length. The aircraft telescopic landing gear comprises a strut, a piston rod, a tire and a hydraulic oil adjusting control system, wherein the piston rod is arranged in the strut; one end of the piston rod extends out of the strut and is connected with the tire; the piston rod comprises an upper piston rod and alower piston rod; the outer side of the upper piston rod is attached to the inner side wall of the strut; a part between the upper piston rod and the strut is filled with an oil medium; a part between the upper surface of the oil medium and the top end of the strut is filled with a gas medium; a first sealing ring is arranged on the upper end side face of the lower piston rod; a second sealing ring is arranged at the bottom end of the strut; a hydraulic oil cavity is formed between the first sealing ring and the second sealing ring; the side wall of the strut is provided with an upper fillerneck and a lower filler neck; the upper filler neck and the lower filler neck are communicated with the hydraulic oil adjusting control system. The aircraft telescopic landing gear disclosed by the invention has the advantages of simple structure, light weight and high bearing capacity; in addition, the aircraft telescopic landing gear is retracted and the length of the aircraft telescopic landinggear is reduced by the hydraulic oil adjusting control system, so that the hydraulic oil adjusting control system can be stored in a smaller landing gear compartment space.

Description

technical field [0001] The invention relates to the technical field of aircraft design, in particular to an aircraft strut landing gear with controllable length. Background technique [0002] At present, the landing gear commonly used on aircraft mainly includes strut landing gear and rocker landing gear (including semi-rocker landing gear). The advantages of the strut landing gear are simple structure, light weight and stronger carrying capacity, but The tire impact force of the strut landing gear is directly transmitted to the piston and the strut, which is pure tension and pressure transmission, and no other mechanism is involved in the force transmission, so the load inside the entire landing gear is relatively small, and the strut and piston only need to be directly It is enough to withstand the impact force of the tire, but at the same time, in order to effectively eliminate the impact energy transmitted by the tire, it is necessary to design the piston rod and the pil...

AI Technical Summary

Problems solved by technology

[0002] At present, the landing gear commonly used on aircraft mainly includes strut landing gear and rocker landing gear (including semi-rocker landing gear). The advantages of the strut landing gear are simple structure, light weight and stronger carrying capacity, but The tire impact force of the strut landing gear is directly transmitted to the piston and the strut, which is pure tension and pressure transmission, and no other mechanism is involved in the force transmission, so the load inside the entire landing gear is relatively small, and the strut and piston only need to be directly It is enough to withstand the impact force of the tire, but at the same time, in order to effectively eliminate the impact energy transmitted by the tire, it is necessary to design the piston rod and the pillar to be relatively long, so that the movement stroke of the piston rod is as large as possible, resulting in the pillar The overall length dimension of the undercarriage is relatively large

Therefore, a space with a long size is required as a landing gear compartment. For a large-tonnage aircraft, the aircraft is large in size, so it is easy to design a long-sized landing gear compartment, but as a small-tonnage aircraft, it is difficult to design a long-sized landing gear compartment Due to the long size of the landing gear compartment, many small-tonnage aircraft have given up the strong-carrying-capacity strut-type landing gear scheme, and adopted rocker-type landing gear or semi-rocker-type landing gear. Through a special mechanism, the undercarriage of the landing gear The rocker arm retracts the landing gear, and then retracts it into the landing gear compartment. At this time, the requirement for the landing gear compartment is to have a suitable length and width. Such a space is relatively easy to design on a small-tonnage aircraft, but the rocker arm type Compared with the strut landing gear, the landing gear has two main load-bearing parts, the strut and the rocker arm, because the impact force from the tires will first be transmitted to the rocker arm, and then it will be enlarged and transmitted to the buffer according to the principle of leverage. It is transmitted to the fuselage by the struts, and this force transmission path will amplify the impact force passing through the tires of the landing gear many times, resulting in a very large internal load of the landing gear, so the weight is much heavier than that of the strut type landing gear. The arm can be shaken, and the rocker landing gear usually designs a mechanism to complete the retraction of the landing gear, so the structure of the rocker landing gear is more complicated

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