Volume 17 (2024)
Volume 16 (2023)
Volume 15 (2022)
Volume 14 (2021)
Volume 13 (2020)
Volume 12 (2019)
Volume 11.1 (2018)
Volume 11 (2017)
Volume 10 (2013)
Volume 9 (2012)
Volume 8 (2011)
Volume 7 (2010)
Volume 6 (2009)
Volume 5 (2008)
Volume 4 (2007)
Volume 3 (2006)
Volume 2 (2005)
Volume 1 (2004)
Number of Articles: 6
A Modified Midcourse Guidance Law Based on Genelarized Collision Course
Volume 3, Issue 3 , September 2006, Pages 113-123
Abstract
Read MoreIn-Trim Flight Investigations of a Conceptual Fluidic Thrust-Vectored Unmanned Tail-Sitter Aircraft
Volume 3, Issue 3 , September 2006, Pages 125-133
Abstract
The feasibility of using a stand alone Fluidic Thrust-Vectoring (FTV) system for the purpose of longitudinal trim of an unmanned aerial vehicle is the focus of the research presented in this paper. Since the fluidic thrust vectoring requires high pressure secondary air to deflect the engine exhaust gases, ... Read MoreCOMPARISON BETWEEN MINIMUM AND NEAR MINIMUM TIME OPTIMAL CONTROL OF A FLEXIBLE SLEWING SPACECRAFT
Volume 3, Issue 3 , September 2006, Pages 135-142
Abstract
In this paper, a minimum and near-minimum time optimal control laws are developed and compared for a rigid space platform with flexible links during an orientating maneuver with large angle of rotation. The control commands are considered as typical bang-bang with multiple symmetrical switches, the time ... Read MoreRobust Integral Sliding-Mode Control of an Aerospace Launch Vehicle
Volume 3, Issue 3 , September 2006, Pages 143-149
Abstract
An analysis of on-line autonomous robust tracking controller based on variable structure control is presented for an aerospace launch vehicle. Decentralized sliding-mode controller is designed to achieve the decoupled asymptotic tracking of guidance commands upon plant uncertainties and external disturbances. ... Read MoreNORMAL FORM SOLUTION OF REDUCED ORDER OSCILLATING SYSTEMS
Volume 3, Issue 3 , September 2006, Pages 153-158
Abstract
This paper describes a preliminary investigation into the use of normal form theory for modelling large non-linear dynamical systems. Limit cycle oscillations are determined for simple two-degree-of-freedom double pendulum systems. The double pendulum system is reduced into its centre manifold before ... Read MoreLaminar and Turbulent Aeroheating Predictions around Multi -Cone Configurations in Hypersonic Equilibrium - Air Flow
Volume 3, Issue 3 , September 2006, Pages 159-166