发明名称 |
AIRCRAFT LANDING GEAR ACTUATOR |
摘要 |
This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. An actuator is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller in communication with the actuator is configured to command the actuator between the stowed and deployed positions in response to an input. The controller commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive. |
申请公布号 |
WO2010009289(A2) |
申请公布日期 |
2010.01.21 |
申请号 |
WO2009US50796 |
申请日期 |
2009.07.16 |
申请人 |
HAMILTON SUNDSTRAND CORPORATION;COLLINS, ANDREW, JOHN |
发明人 |
COLLINS, ANDREW, JOHN |
分类号 |
B64C25/10;H02K7/00 |
主分类号 |
B64C25/10 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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