scholarly journals Achieving load relief with minimal change in conventional control law of a launch vehicle

2016 ◽  
Vol 49 (1) ◽  
pp. 361-366 ◽  
Author(s):  
Gopal Jee ◽  
V. Brinda ◽  
V.R. Lalithambika ◽  
M.V. Dhekane
Keyword(s):  
Launch Vehicle ◽  
Minimal Change ◽  
Control Law ◽  
Load Relief

Load relief control of launch vehicle using aerodynamic angle estimation

2017 ◽  
Vol 232 (8) ◽  
pp. 1598-1605
Author(s):  
Gyeongtaek Oh ◽  
Jongho Park ◽  
Jeongha Park ◽  
Hongju Lee ◽  
Youdan Kim ◽  
...  
Keyword(s):  
Closed Loop ◽  
Sliding Mode ◽  
Dynamic Pressure ◽  
Launch Vehicle ◽  
Aerodynamic Load ◽  
Load Relief ◽  
Control Scheme ◽  
Potential Benefits ◽  
Aerodynamic Angle ◽  
Ascent Phase

A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.

LQG Controller for Load Relief Control of a Flexible Launch Vehicle

2019 ◽  
Author(s):  
Ammu Prameela Nandakumar ◽  
Lalu Seban ◽  
Rajesh Joseph Abraham ◽  
M V Dhekane
Keyword(s):  
Launch Vehicle ◽  
Load Relief

Evolution of attitude control law of an Indian re-entry launch vehicle

2014 ◽  
Vol 6 (3-4) ◽  
pp. 148-157 ◽  
Author(s):  
Gopal Jee ◽  
Kapil Kumar Sharma ◽  
K. Koteswara Rao ◽  
Sam K. Zachariah ◽  
V. Brinda ◽  
...  
Keyword(s):  
Attitude Control ◽  
Launch Vehicle ◽  
Control Law

scholarly journals Finite-time observer-based backstepping control of a flexible launch vehicle

2016 ◽  
Vol 24 (8) ◽  
pp. 1535-1550 ◽  
Author(s):  
Elodie Duraffourg ◽  
Laurent Burlion ◽  
Tarek Ahmed-Ali
Keyword(s):  
Finite Time ◽  
Launch Vehicle ◽  
Backstepping Control ◽  
Control Law ◽  
Beam Model ◽  
Flexible Mode ◽  
Space Launch ◽  
Rigid Model ◽  
Euler Bernoulli Beam ◽  
Bernoulli Beam Model

In this paper, a longitudinal model of a space launch vehicle was developed using the Lagrange mechanism and a free–free Euler–Bernoulli beam model. The aim was to propose a model including one flexible mode plus a nonlinear aerodynamic coefficient for nonlinear control design. We then studied the output feedback problem raised by using such a nonlinear model. The main achievement is to propose a new finite-time state observer when the measured outputs are corrupted by an unidentified flexible mode. This effect may destabilize a classical backstepping control law applied to the rigid model. To achieve this, a backstepping control law was redesigned to damp out the flexible mode, once measured and characterized. Hence a new adaptive finite time observer was developed. Closed-loop simulations show the effectiveness of the observer in combination with a redesigned backstepping control law when sensors and the launcher nozzle are collocated.

Robustness analysis of a reusable launch vehicle flight control law

2009 ◽  
Vol 17 (7) ◽  
pp. 751-765 ◽  
Author(s):  
P.P. Menon ◽  
I. Postlethwaite ◽  
S. Bennani ◽  
A. Marcos ◽  
D.G. Bates
Keyword(s):  
Flight Control ◽  
Robustness Analysis ◽  
Launch Vehicle ◽  
Control Law ◽  
Reusable Launch Vehicle

Load Relief Control of H-IIA Launch Vehicle

2004 ◽  
Vol 37 (6) ◽  
pp. 985-990 ◽  
Author(s):  
Hideto Suzuki
Keyword(s):  
Launch Vehicle ◽  
Load Relief
Sign in / Sign up

Export Citation Format

Share Document