Books on the topic 'Thrust vector'

Leitner, A. Thrust vector control, heat transfer modeling. Monterey, California: Naval Postgraduate School, 1986.

Green, Robert S. Measured pressure distributions inside nonaxisymmetric nozzles with partially deployed thrust reversers. Hampton, Va: Langley Research Center, 1987.

Mason, Mary L. A static investigation of the thrust vectoring system of the F/A-18 high-alpha research vehicle. Hampton, Va: Langley Research Center, 1992.

Asbury, Scott C. Multiaxis thrust-vectoring characteristics of a model representative of the F-18 High-Alpha Research Vehicle at angles of attack from 0 deg to 70 deg. Hampton, Va: Langley Research Center, 1995.

Nunn, R. H. TVC jet vane thermal modeling using parametric system identification. Monterey, Calif: Naval Postgraduate School, 1988.

Reno, Margaret Mary. Modeling transient thermal behavior in a thrust vector control jet vane. Monterey, Calif: Naval Postgraduate School, 1988.

Gilyard, Glenn B. Optimal pitch thrust-vector angle and benefits for all flight regimes. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

Quinto, P. Frank. Evaluation of four advanced nozzle concepts for short takeoff and landing performance. Hampton, Va: Langley Research Center, 1993.

Asbury, Scott C. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. Hampton, Va: Langley Research Center, 1993.

Bangert, Linda S. Static internal performance of a nonaxisymmetric vaned thrust reverser with flow splay capability. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

Asbury, Scott C. Multiaxis thrust-vectoring characteristics of a model representative of the F-18 High-Alpha Research Vehicle at angles of attack from 0 ̊to 70h̊. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Goodrich, Kenneth H. A closed-form trim solution yielding minimum trim drag for airplanes with multiple longitudinal-control effectors. Hampton, Va: Langley Research Center, 1989.

E, Johnson Richard. Effects of thrust vector control on the performance of the aerobang orbital plane change maneuver. Monterey, Calif: Naval Postgraduate School, 1993.

Imlay, Scott T. Implicit time-marching solution of the Navier-Stokes equations for thrust reversing and thrust vectoring nozzle flows. Hampton, Va: Langley Research Center, 1986.

Reubush, David E. Effects of the installation and operation of jet-exhaust yaw vanes on the longitudinal and lateral-directional characteristics of the F-14 airplane. Hampton, Va: Langley Research Center, 1987.

Wing, David J. Static investigation of a multiaxis thrust-vectoring nozzle with variable internal contouring ability. Washington, D.C: National Aeronautics and Space Administration, 1997.

Johnson, Steven A. A simple dynamic engine model for use in a real-time aircraft simulation with thrust vectoring. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

C, Murphy Patrick. A control law design method facilitating control power, robustness, agility, and flying qualities tradeoffs, CRAFT. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

Foley, Robert J. Static thrust-vectoring performance of nonaxisymmetric convergent-divergent nozzles with post-exit yaw vanes. Hampton, Va: Langley Research Center, 1991.

Mark, Greaney, ed. Threat vector. London: Penguin Books, 2013.

Mark, Greaney, ed. Threat vector. New York: G.P. Putnam's Sons, 2012.

DiMercurio, Michael. Threat vector. New York: Onyx Book, 2000.

Nelms, R. M. Design of power electronics for TVC & EMA systems: Final report. [Washington, DC: National Aeronautics and Space Administration, 1994.

Rawlin, Vincent K. Xenon ion propulsion for orbit transfer. [Washington, DC]: National Aeronautics and Space Administration, 1990.

Carpenter, Thomas. Evaluation of dual flow, thrust vector nozzles with exhaust stream impingement: Semi-annual progress report 6/92-12/92, NASA-Ames grant number NAG 2-778. San Luis Obispo, Calif: California Polytechnic State University, 1992.

Electromechanical actuation for thrust vector control applications. [Washington, D.C.]: NASA, 1990.

Yukselen, Alp. Heat transfer modelling of thrust vector control systems. 1986.

Optimal pitch thrust-vector angle and benefits for all flight regimes. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

Alexander, Bolonkin, and NASA Dryden Flight Research Center., eds. Optimal pitch thrust-vector angle and benefits for all flight regimes. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

Alexander, Bolonkin, and NASA Dryden Flight Research Center., eds. Optimal pitch thrust-vector angle and benefits for all flight regimes. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

Dulke, Michael F. Heat transfer modeling of jet vane Thrust Vector Control (TVC) Systems. 1987.

Optimal pitch thrust-vector angle and benefits for all flight regimes. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

Alexander, Bolonkin, and NASA Dryden Flight Research Center., eds. Optimal pitch thrust-vector angle and benefits for all flight regimes. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

United States. National Aeronautics and Space Administration., ed. Independent Orbiter assessment: Assessment of the ascent thrust vector control actuator subsystem. [Washington, DC?: National Aeronautics and Space Administration, 1990.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

1935-, Lan C. Edward, and United States. National Aeronautics and Space Administration., eds. Semi-annual status report on NASA grant NAG 1-837, "Aerodynamics of thrust vectoring": June 11, 1989-December 10, 1989. Lawrence, Kan: Flight Research Laboratory, University of Kansas Center for Research, 1989.

Center, Langley Research, ed. Static performance investigation of a skewed-throat multiaxis thrust-vectoring nozzle concept. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

J, Capone Francis, and Langley Research Center, eds. Multiaxis thrust-vectoring characteristics of a model representative of the F-18 High-Alpha Research Vehicle at angles of attack from 0 ̊to 70 ̊. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

M, Sliwa Steven, Lallman Frederick J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. A closed-form trim solution yielding minimum trim drag for airplanes with multiple longitudinal-control effectors. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

J, Capone Francis, and Langley Research Center, eds. Multiaxis thrust-vectoring characteristics of a model representative of the F-18 High-Alpha Research Vehicle at angles of attack from 0 ̊to 70 ̊. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

M, Sliwa Steven, Lallman Frederick J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. A closed-form trim solution yielding minimum trim drag for airplanes with multiple longitudinal-control effectors. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

A closed-form trim solution yielding minimum trim drag for airplanes with multiple longitudinal-control effectors. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

Static performance of a fixed-geometry exhaust nozzle incorporating porous cavities for shock-boundary layer interaction control. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

United States. National Aeronautics and Space Administration., ed. An experimental/modeling study of jet attachment during counterflow thrust vectoring: Final report, NASA/NAG1-1736, grant period 1 July, 1995 - 30 June, 1996. [Washington, DC: National Aeronautics and Space Administration, 1997.

A, Hunter Craig, and Langley Research Center, eds. Static performance of a fixed-geometry exhaust nozzle incorporating porous cavities for shock-boundary layer interaction control. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

United States. National Aeronautics and Space Administration., ed. An experimental/modeling study of jet attachment during counterflow thrust vectoring: Final report, NASA/NAG1-1736, grant period 1 July, 1995 - 30 June, 1996. [Washington, DC: National Aeronautics and Space Administration, 1997.

D, Leavitt Laurence, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Static internal performance of a thrust vectoring and reversing two-dimensional convergent-divergent nozzle with an aft flap. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

Aeroservoelastic modeling and validation of a thrust-vectoring F/A-18 aircraft. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.