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Small aircraft landing assisting device

An auxiliary device and aircraft technology, which is applied in the field of aircraft engineering, can solve problems such as poor stability, and achieve the effect of avoiding north wind blowing and protecting the aircraft

Inactive Publication Date: 2017-02-22
隋东昊
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

After the aircraft lands, it directly stays at the docking position. In weather such as strong winds, the aircraft will be blown and moved, and the stability is poor.

Method used

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  • Small aircraft landing assisting device
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Embodiment Construction

[0012] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0013] The small-sized aircraft landing auxiliary device, as shown in the figure, includes a support base 1, a bowl-shaped receiving platform 2 is installed on the top of the support base 1, and a lifting base 3 is installed on the bottom of the support base 1, and the bottom of the lifting base 3 is a lifting mechanism. The mechanism can be a...

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Abstract

A small aircraft landing assisting device comprises a supporting base. A bowl-shaped carrying table is installed on the upper portion of the supporting base. A lifting base is installed at the bottom of the supporting base. A lifting mechanism is arranged on the lower portion of the lifting base. A plurality of locking buckle devices are installed on the lifting base evenly and annularly. Each locking buckle device comprises two blades and an electric push rod, wherein the lower portions of the blades are hinged to the lifting base, the electric push rod is located on the outer sides of the blades, the lower end of the electric push rod is hinged to the lifting base, the upper end of the electric push rod is hinged to the side edges of the blades, and hemispherical protruding blocks are arranged on the inner sides of the blades. The assisting device also comprises an annular locking device at the bottom of an aircraft, the locking device is composed of two rings including the inner ring and the outer ring, the lower ends of the sections of the rings are folded outward to form a hook shape, and the protruding blocks on the blades can be matched with the hook-shaped parts of the rings. The assisting device is particularly suitable for aircrafts low in fuel amount or electric quantity to land, and the aircrafts can be protected after landing and wait for being taken away by related personnel.

Description

technical field [0001] The invention belongs to the field of aircraft engineering, in particular to a landing auxiliary device for a small aircraft. Background technique [0002] The landing process of small aircraft needs to be very careful to avoid damage to the aircraft. For remote operation, it is more troublesome. The aircraft stays at the docking position directly after landing. In weather such as strong winds, the aircraft will be blown and moved, resulting in poor stability. SUMMARY OF THE INVENTION [0003] The invention provides a small aircraft landing assist device to solve the defects in the prior art. [0004] The present invention is achieved through the following technical solutions: [0005] A small aircraft landing auxiliary device, including a support seat, a bowl-shaped receiving platform is installed on the upper part of the support seat, a lifting seat is installed on the bottom of the support seat, and the lower part of the lifting seat is a lifti...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F1/36B64C25/06
CPCB64F1/02B64C25/06
Inventor 隋东昊
Owner 隋东昊
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