NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Fluidic Emergency Thruster for AircraftThe design, development, fabrication and test evaluation of two prototype fluidic emergency thrusters (FET) for aircraft stabilization are discussed. The fluidic control units were designed to provide, between two diametrically opposed nozzles, a thrust differential proportional to an input voltage signal. The emergency roll control requirements of the X-14 VTOL research aircraft were defined as typical design goals. Two control units, one on each wing tip, are intended to provide a maximum thrust of 224 pounds per unit. The units are designed to operate with 2500 psig, 2000 F gas from a solid propellant gas generator. The emergency system including the gas generator was designed to add less than 11 pounds per wing tip. The operating time under emergency conditions was specified as five seconds. The fluidic emergency thruster is similar in concept to a JATO system but has the added feature of controllable thrust.
Document ID
19730003314
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Honda, T. S. (General Electric Co. Schenectady, NY, United States)
Date Acquired
September 2, 2013
Publication Date
November 1, 1972
Subject Category
Aircraft
Report/Patent Number
NASA-CR-114490
Accession Number
73N12041
Funding Number(s)
CONTRACT_GRANT: NAS2-5467
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available