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Crank floating type hatch door actuating mechanism

An actuating mechanism and floating technology, applied in the field of aviation electromechanical, can solve the problems of unreliable action, complex structure, and many components, and achieve the effect of rapid intermediate movement, soft start and position, and few components

Active Publication Date: 2019-04-02
JINCHENG NANJING ELECTROMECHANICAL HYDRAULIC PRESSURE ENG RES CENT AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the existing door actuating mechanism either cannot realize the above functions, or has many components and complex structure, so the action is unreliable

Method used

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  • Crank floating type hatch door actuating mechanism
  • Crank floating type hatch door actuating mechanism

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Embodiment Construction

[0012] In order to understand the purpose, technical solutions and advantages of the present invention more clearly, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0013] figure 1 It is a structural schematic diagram of the crank-floating hatch door actuating mechanism of the present invention. Such as figure 1 , the crank floating hatch door actuating mechanism of the present invention comprises a drive shaft 1, a connector 2 (in this embodiment, a ring is used), a cylinder 3, a crank 4, a sleeve 5, a support rod 6 and a hatch shaft 7. The drive shaft 1 is perpendicular to the hatch shaft 7 . The ring 2 is coaxially installed on the drive shaft 1. The drive shaft 1, the ring 2 and the cylinder 3 are connected to form a rigid body, and the axis MN of the cylinder 3 is parallel to the axis of the drive shaft 1 with a distance N. The sleeve 5, the support rod 6 and the hatch 8 are connected to...

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Abstract

The invention discloses a crank floating type hatch door actuating mechanism. A drive shaft (1) is perpendicular to a hatch door shaft (7), a connector (2) is mounted on the drive shaft (1), and connected to a cylinder (3), the drive shaft (1), the connector (2) and the cylinder (3) are connected to form a rigid body, the axis of the cylinder (3) is parallel to the axis of the drive shaft (1), a sleeve (5), a support rod (6) and a hatch door (8) are connected to form a rigid body, the axis of the sleeve (5) is parallel to the axis of the hatch door shaft (7), the hatch door shaft (7) passes through the support rod (6) and is fixed on the body, two end straight rod sections of the crank (4) are respectively inserted into the cylinder (3) and the sleeve (5), and the inner hole length L of the sleeve (5) is greater than 2N, and N is the distance between the axis of the cylinder (3) and the axis of the drive shaft (1). The mechanism has few components, is simple and reliable, and the opening and closing action has the sinusoidal characteristics of rapid intermediate movement, soft starting and positioning.

Description

technical field [0001] The invention belongs to the field of aviation electromechanical technology, in particular to a crank-floating cabin door actuating mechanism. Background technique [0002] Door actuation mechanisms are widely used on aircraft and other carrying equipment. According to the requirements of door shape, opening and closing positions, and motion characteristics, there are various forms, such as hydraulic or electric drive actuators, hinged linkages, etc. formula etc. [0003] Some equipment requires that the door gradually accelerates after opening at a selected minimum speed, and decelerates to the position before reaching the maximum opening position; during closing, the door starts to move at a minimum speed and then gradually accelerates, and closes the door at a minimum speed. However, the existing hatch door actuating mechanisms either cannot realize the above functions, or have many components and complex structures, so the actions are unreliable. ...

Claims

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Application Information

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IPC IPC(8): B64C1/14
CPCB64C1/14
Inventor 刘晓东张维峰陈屹
Owner JINCHENG NANJING ELECTROMECHANICAL HYDRAULIC PRESSURE ENG RES CENT AVIATION IND OF CHINA
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