A strut landing gear with controllable length

Abstract

The invention discloses an aircraft strut-type landing gear with controllable length, which comprises a strut, a piston rod, a tire and a hydraulic oil adjustment control system. A piston rod is arranged inside the strut, and one end of the piston rod protrudes from the strut to connect with the tire. Divided into an upper piston rod and a lower piston rod, the outer side of the upper piston rod is close to the inner wall of the pillar, the upper piston rod and the pillar are filled with oil medium, the upper surface of the oil medium and the top of the pillar is filled with gas medium, and the lower piston rod There is a first sealing ring on the side of the upper end, and a second sealing ring on the bottom of the pillar. A hydraulic oil cavity is formed between the first sealing ring and the second sealing ring. The side wall of the pillar is provided with an upper nozzle and a lower nozzle. The nozzle, the upper nozzle and the lower nozzle communicate with the hydraulic oil adjustment control system. The strut type landing gear of the present invention has the advantages of simple structure, light weight and strong bearing capacity, and can be accommodated in a smaller space of the landing gear cabin by shrinking it through the hydraulic oil adjustment control system to reduce the length.

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

Images