Aeroelastic Stability of a Slender Missile with Constant Thrust
نویسندگان
چکیده
منابع مشابه
A Study of Dynamic Aeroelastic Effects on the Stability Control and Gust Response of a Slender Delta Aircraft
In this report four previously unpublished notes, concerned with aeroelastic effects on a particular slender delta aircraft configuration, are collected together. Some general flutter calculations show that decreasing stiffness leads to instability in the aircraft short period mode whilst the higher frequency modes remain stable. The reasons for the instability and the implications regarding ai...
متن کاملDetermination of the Stability Constant of Vanadium (V) with Alaine
Formation equilibria of dioxy vanadium (V) complex with alanine in acidic media (pH<2.3) has been investigated potentiometrically and spectrophotometrically. In this condition the 1:1 complex has the formula VO2Y, where Y¯ represent the fully dissociated aminocarboxylate anion. The stability constant of VO2Y was determined as log KVO2Y=11.32±<e...
متن کاملExo-atmospheric Discrimination of Thrust Termination Debris and Missile Segments
his article explores a time-delay neural network (TDNN) for exo-atmospheric discrimination of a missile reentry vehicle (RV) from other missile parts and thrust termination debris. The TDNN is an enhanced version of a back-propagation neural network that accounts for the features in the time domain by using the rate of change of the infrared signature over several seconds as a discriminant. We ...
متن کاملStability of Gravity with a Cosmological Constant
The stability properties of Einstein theory with a cosmological constant A are investigated. For A > 0, stability is established for small fluctuations, about the de Sitter background, occurring inside the event horizon and semiclassical stability is anal~ed. For A < 0, stability is demonstrated for all asymptotically anti-de Sitter metrics. The analysis is based on the general construction of ...
متن کاملHelicopter Blade Stability Analysis Using Aeroelastic Frequency Response Functions
In the present paper, the aeroelastic stability of helicopter rotor blade is determined using Aeroelastic Frequency Response Function. The conventional methods of aeroelastic stability usually use an iterative procedure while the present method does not require such approach. Aeroelastic Frequency Response Functions are obtained by inverting dynamic stiffness matrix of the aeroelastic system. S...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Procedia Engineering
سال: 2012
ISSN: 1877-7058
DOI: 10.1016/j.proeng.2012.01.1002