The invention discloses an
aircraft landing buffer device which comprises pneumatic resistance
speed reduction devices, a distributed bionic four-foot adjusting mechanism, a buffer layer and a central controller which are symmetrically arranged in the circumferential direction, and all modules achieve multi-stage buffer control through position
layout and function
coupling. The aerodynamic resistance
speed reduction device is circumferentially arranged on the edge of the
chassis, aerodynamic pre-deceleration is provided through a resistance plate with an adjustable unfolding angle, landing
kinetic energy is consumed, and
crosswind loads are balanced. The bionic four-foot adjusting mechanisms are distributed at the four corners of the
chassis, joint rigidity and friction damping are adjusted in real
time based on
terrain perception, and uniform distribution of
impact loads of different terrains is achieved. The buffer layer is located between the
chassis and the passenger compartment, and gradient
energy consumption is carried out to control the
impact overload
peak value. By means of intelligent angle adjustment and
crosswind compensation of the pneumatic resistance device, the low-altitude
speed reduction efficiency and the wind resistance capacity are improved; the gradient
energy consumption design of the bionic four feet and the buffer layer solves the adaptability problem of a traditional device landing on the hard ground or the soft ground.