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Rear fuselage protection system

A technology for protecting the system and the tail of the fuselage, which is applied in the direction of aircraft landers, etc., to achieve the effect of improving aerodynamic performance, wide application range, and good aerodynamic shape

Active Publication Date: 2016-03-30
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a fuselage tail protection system to solve or at least alleviate at least one problem in the background art

Method used

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  • Rear fuselage protection system
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Embodiment Construction

[0019] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a rear fuselage protection system, which relates to the technical field of airplane tail protection. The rear fuselage protection system comprises a mechanical part and a control part, wherein the mechanical part comprises an actuator, a rocking arm, a linkage mechanism, a sliding cover and a rail; a piston rod of the actuator is connected with the rocking arm, and the other end, which is opposite to the piston rod, of the actuator is fixed to a fuselage; the rocking arm is connected to the fuselage by virtue of a rotating shaft and can rotate around the rotating shaft, and a roller is arranged on the other end, which is opposite to the rotating shaft, of the rocking arm; one end of the linkage mechanism is fixed to the rocking arm, and the other end of the linkage mechanism is fixed to the sliding cover; the control part is used for controlling the rocking arm to retract and extend. The rear fuselage protection system has the beneficial effects that in normal flight of an airplane, the mechanical part is retracted in the fuselage, when the airplane takes off or lands, if a signal of the control part is received by the mechanical part, the rocking arm extends to protect the rear fuselage, and when the airplane takes off, the rocking arm is retracted, so that the airplane is in a good aerodynamic shape, and the aerodynamic performance is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft tail protection, in particular to a fuselage tail protection system. Background technique [0002] When an aircraft takes off / lands at a relatively large angle of attack, the tail of the fuselage may touch the ground. In order to protect the fuselage structure, protective devices are usually designed on the lower part of the fuselage. At present, the protection devices are all equipped with a protruding protective block at the lower part of the fuselage. According to the different energy absorption methods, they can be divided into two categories: the first type is rigid protection device; the second type is flexible protection device. When the tail of the fuselage is close to the ground, the protective device touches the ground first, and the first type of protective device is rigidly connected with the fuselage, and the vibration and damage to the fuselage are relatively large when it touches t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D45/06
CPCB64D45/06
Inventor 赵志伟赵纯李臣孙卫涛
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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