NDLI: Hydraulic actuator mechanism to control aircraft spoiler movements through dual input commands

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Hydraulic actuator mechanism to control aircraft spoiler movements through dual input commands

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1981
Description	An aircraft flight spoiler control mechanism is described. The invention enables the conventional, primary spoiler control system to retain its operational characteristics while accommodating a secondary input controlled by a conventional computer system to supplement the settings made by the primary input. This is achieved by interposing springs between the primary input and the spoiler control unit. The springs are selected to have a stiffness intermediate to the greater force applied by the primary control linkage and the lesser resistance offered by the spoiler control unit. Thus, operation of the primary input causes the control unit to yield before the springs, yet, operation of the secondary input, acting directly on the control unit, causes the springs to yield and absorb adjustments before they are transmitted into the primary control system.
File Size	410031
Page Count	5
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19820016329
Archival Resource Key	ark:/13960/t1ng9g653
Language	English
Publisher Date	1981-06-09
Access Restriction	Open
Subject Keyword	Aircraft Stability And Control Pistons Actuators Aircraft Hydraulic Systems Manual Control Servocontrol Springs Elastic Automatic Control Servomechanisms Flight Control Spoilers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Patent

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