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  • 1
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    Fluidic emergency roll control system (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fluidic emergency roll control system for aircraft stabilization in the event of primary flight control failure was evaluated. The fluidic roll control units were designed to provide roll torque proportional to an electrical command as operated by two diametrically opposed thrust nozzles located in the wing tips. The control package consists of a solid propellant gas generator, two diametrically opposed vortex valve modulated thrust nozzles, and an electromagnetic torque motor. The procedures for the design, development, and performance testing of the system are described.
    Keywords: AIRCRAFT
    Type: NASA-CR-114588
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Vortex servovalve for fluidic or electrical input (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Proportional-pressure control servovalve consisting of fluid amplifier bellows-driven jet-pipe and two vortex valves operating in push-pull, with a pair of bellows for pressure feedback is tolerant to comtaminant particles and meets minimum standby flow requirements for applications such as rocket thruster nozzles.
    Keywords: MACHINERY
    Type: ARC-10155
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Fluidic Emergency Thruster for Aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The 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.
    Keywords: AIRCRAFT
    Type: NASA-CR-114490
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Fluidic proportional thruster for SPARCS 4 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design, development, fabrication, and acceptance test results for two fluidic proportional thrusters for use in SPARCS 4
    Keywords: SPACE VEHICLES
    Type: NASA-CR-114333 , S-71-1084
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Fluidic Proportional Thruster System Final Report (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fluidic proportional thrust control system with vortex valves
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-73304 , S-69-1079
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A new reaction control approach for sounding rockets (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: High performance reaction pointing control systems for sounding rockets, using proportional control of differential thrust and adaptive control of thrust magnitude
    Keywords: SPACE VEHICLES
    Type: SAE PAPER 700783 , SOCIETY OF AUTOMOTIVE ENGINEERS, NATIONAL AERONAUTIC AND SPACE ENGINEERING AND MFG. MEETING; Oct 05, 1970 - Oct 09, 1970; LOS ANGELES, CA
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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