Linkage mechanism for driving aircraft landing gear bay door

US9868519B2 · kind B2 · utility

Assignee

• COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD. SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE · CN

Inventors

• Jun Lv · Lo Wu, CN
• Qinggong Meng · Shanghai, CN
• Pu Zhang
• Hao Jiang · 安丰镇, CN
• Shangxin Yang · Shanghai, CN
• Hengkang Zhang · Shanghai, CN
• Jian Ma · Nanhu, CN

Key dates

• Filing date: Aug 20, 2014
• Grant date: Jan 16, 2018
• Expiry date: Apr 19, 2035

Classification

• Technology area (CPC B): Performing Operations; Transporting
• CPC primary: B64C25/16
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column to the primary torsion tube. A secondary torsion tube has an inner end portion located inside the hatch and an outer end portion located outside the hatch. A second drive apparatus is located outside the landing gear hatch and connects the primary torsion tube and the secondary torsion tube outside the hatch. Two third drive apparatuses are connected between the inner end portion of the secondary torsion tube and one of the hatch doors.