نتایج جستجو برای: reusable launch vehicle

تعداد نتایج: 134148  

1997
W. D. Morris N. H. White W. T. Davis

Methods exist to define the logistics support requirements for new aircraft concepts but are not directly applicable to new launch vehicle concepts. In order to define the support requirements and to discriminate among new technologies and processing choices for these systems, NASA Langley Research Center (LaRC) is developing new analysis methods. This paper describes several methods under deve...

2001
A. C. Charania Jon Wallace John R. Olds Edgar Zapata John F. Kennedy

Designers of space launch systems should be cognizant of the impact of their design assumptions on operational characteristics. Operational metrics such as turnaround time, recurring cost, and headcount are critical factors for the future viability of such systems. The results presented here are from a study that seeks to determine in what manner design approaches can improve the operability of...

2013
S JAYAKRISHNAN R HARIKUMAR

A major objective of next generation reusable launch vehicle (RLV) programs includes significant improvements in vehicle safety, reliability, and operational costs. In this paper, trajectory generation on approach/landing (A&L) for RLVs using motion primitives (MPs) and neighboring optimal control (NOC) is discussed. The proposed trajectory generation approach at A&L phase is based on an MP sch...

Journal: :Journal of the Japan Society for Aeronautical and Space Sciences 1998

Journal: :Journal of the Japan Society for Aeronautical and Space Sciences 1998

2004
P. P. Friedmann K. G. Powell

The hypersonic aeroelastic and aerothermoelastic problem of a double-wedge airfoil typical cross-section is studied using three different unsteady aerodynamic loads: (1) third-order piston theory, (2) Euler aerodynamics, and (3) Navier-Stokes aerodynamics. Computational aeroelastic response results are used to obtain frequency and damping characteristics, and compared with those from piston the...

Journal: :TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2012

Journal: :Journal of the Society of Materials Science, Japan 1988

Journal: :Journal of the Japan Society for Aeronautical and Space Sciences 1990

Journal: :CoRR 2016
Antonio Graells Francisco Carrabina

Atmospheric flight phase of a launch vehicle is utilized to evaluate the performance of an H∞ controller in the presence of disturbances. Dynamics of the vehicle is linearly modeled using time-varying parameters. An operating point was found to design a robust command tracker using H∞ control theory that guarantees a stable maneuver. At the end, the controller was employed on the launch vehicle...

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