Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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AIRCRAFT STABILITY AND CONTROL
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20000064689 NASA Marshall Space Flight Center, Huntsville, AL USA
X-33 Ascent Flight Controller Design by Trajectory Linearization: A Singular Perturbational Approach
Zhu, J. Jim, Louisiana State Univ., USA; Banker, Brad D., Louisiana State Univ., USA; Hall, Charles E., NASA Marshall Space
Flight Center, USA; [2000]; 7p; In English; Guidance, Control and Dynamics, 2000, Reston, VA, USA; Sponsored by American
Inst. of Aeronautics and Astronautics, USA; Copyright Waived; Avail: CASI; A02, Hardcopy; A01, Microfiche
The flight control of X-33 poses a challenge to conventional gain-scheduled flight controllers due to its large attitude maneuvers
from liftoff to orbit and reentry. In addition, a wide range of uncertainties in vehicle handling qualities and disturbances must
be accommodated by the attitude control system. Nonlinear tracking and decoupling control by trajectory linearization can be
viewed as the ideal gain-scheduling controller designed at every point on the flight trajectory. Therefore it provides robust stability
and performance at all stages of flight without interpolation of controller gains and eliminates costly controller redesigns due to
minor airframe alteration or mission reconfiguration. In this paper, a prototype trajectory linearization design for an X-33 ascent
flight controller is presented along with 3-DOF and 6-DOF simulation results. It is noted that the 6-DOF results were obtained
from the 3-DOF design with only a few hours of tuning, which demonstrates the inherent robustness of the design technique. It
is this ”plug-and-play” feature that is much needed by NASA for the development, test and routine operations of the RLV’S. Plans
for further research are also presented, and refined 6-DOF simulation results will be presented in the final version of the paper.
Author
Approach Control; Attitude Control; Controllability; Flight Control; Prototypes; Simulation; X-33 Reusable Launch Vehicle
09
RESEARCH AND SUPPORT FACILITIES (AIR)
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20000061489 NASA Langley Research Center, Hampton, VA USA
Simultaneous Global Pressure and Temperature Measurement Technique for Hypersonic Wind Tunnels
Buck, Gregory M., NASA Langley Research Center, USA; [2000]; 14p; In English; 21st; Aerodynamic Measurement Technology
and Ground Testing, 19-22 Jun. 2000, Denver, CO, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA
Report No.(s): AIAA Paper 2000-2649; Copyright Waived; Avail: CASI; A03, Hardcopy; A01, Microfiche
High-temperature luminescent coatings are being developed and applied for simultaneous pressure and temperature mapping
in conventional-type hypersonic wind tunnels, providing global pressure as well as Global aeroheating measurements. Together,
with advanced model fabrication and analysis methods, these techniques will provide a more rapid and complete experimental
aerodynamic and aerothermodynamic database for future aerospace vehicles. The current status in development of simultaneous
pressure- and temperature-sensitive coatings and measurement techniques for hypersonic wind tunnels at Langley Research Center
is described. and initial results from a feasibility study in the Langley 31-Inch Mach 10 Tunnel are presented.
Author
Pressure Measurement; Temperature Measurement; Aerodynamic Heating
20000062013 NASA Langley Research Center, Hampton, VA USA
Overview of Selected Measurement Techniques for Aerodynamics Testing in the NASA Langley Unitary Plan Wind Tunnel
Erickson, Gary E., NASA Langley Research Center, USA; [2000]; 56p; In English; Fluids, 19-22 Jun. 2000, Denver, CO, USA;
Sponsored by American Inst. of Aeronautics and Astronautics, USA; Original contains color illustrations
Report No.(s): AIAA Paper 2000-2396; Copyright Waived; Avail: CASI; A04, Hardcopy; A01, Microfiche
An overview is given of selected measurement techniques used in the NASA Langley Research Center (LaRC) Unitary Plan
Wind Tunnel (UPWT) to determine the aerodynamic characteristics of aerospace vehicles operating at supersonic speeds. A broad
definition of a measurement technique is adopted in this paper and is any qualitative or quantitative experimental approach that
provides information leading to the improved understanding of the supersonic aerodynamic characteristics. On-surface and off-