Guidance and robust generalized inversion based attitude control of Satellite Launch Vehicle

2016 ◽  
Author(s):  
Uzair Ansari ◽  
Abdulrahman H. Bajodah
Keyword(s):  
Attitude Control ◽  
Launch Vehicle ◽  
Generalized Inversion ◽  
Satellite Launch Vehicle

Launch vehicle ascent flight attitude control using direct adaptive generalized dynamic inversion

2018 ◽  
Vol 233 (11) ◽  
pp. 4141-4153 ◽  
Author(s):  
Uzair Ansari ◽  
Abdulrahman H Bajodah
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Launch Vehicle ◽  
Dynamic Scaling ◽  
Dynamic Inversion ◽  
Continuous Control ◽  
Attitude Tracking ◽  
Yaw Attitude ◽  
Satellite Launch Vehicle ◽  
Control Part

This paper presents the attitude control design of satellite launch vehicle based on the direct adaptive generalized dynamic inversion approach. The proposed adaptive generalized dynamic inversion approach encompasses the equivalent and the adaptive control elements. The equivalent (continuous) control part of adaptive generalized dynamic inversion is based on the conventional generalized dynamic inversion approach that comprises two noninterfering control actions, i.e. the particular part and the auxiliary part. In the particular part, dynamical constraint is prescribed in the form of time differential equation, which is evaluated along the vehicle attitude trajectories that encapsulates the control objectives and is inverted by utilizing Moore Penrose Generalized Inverse (MPGI). The singularity problem is solved by augmenting a dynamic scaling factor in the involved MPGI. In the auxiliary part, the null control vector is designed using the proportionality gain matrix, constructed by employing the Lyapunov function that guarantees global closed-loop asymptotic stability of the angular body rate dynamics. The adaptive (discontinuous) control part of adaptive generalized dynamic inversion is based on the sliding mode control with adaptive modulation gain, that provides robustness against tracking performance deterioration due to generalized scaling, system nonlinearities, and uncertainties, such that semi-global practically stable attitude tracking is guaranteed. External guidance loop based on the trajectory following method is designed, which reshapes the predefined pitch and yaw attitude profiles based on the respective normal and lateral positional errors, for acquiring the desired orbital parameters such as height, injection angle, orbital velocity, etc. To analyze the ascent flight trajectory, a detailed six-degrees-of-freedom simulator of a four-stage satellite launch vehicle is developed. The intensive numerical simulations are performed, which demonstrate the stability, robustness and the tracking capability of the proposed control and guidance methods in the presence of parametric uncertainties and external disturbances.

A fault-tolerant computer system for India’s satellite launch vehicle programmes

Sadhana ◽  
1987 ◽  
Vol 11 (1-2) ◽  
pp. 221-231 ◽  
Author(s):  
D. Basu ◽  
K. V. S. S. Prasad Rao ◽  
S. V. L. A. Varaprasad ◽  
T. Kurian ◽  
T. Jayasri ◽  
...  
Keyword(s):  
Computer System ◽  
Fault Tolerant ◽  
Launch Vehicle ◽  
Satellite Launch Vehicle

Failure Analysis of AISI 440C Steel Ball Screws Used in the Actuator System of a Satellite Launch Vehicle

2017 ◽  
Vol 17 (3) ◽  
pp. 505-512 ◽  
Author(s):  
Sushant K. Manwatkar ◽  
A. Bahrudheen ◽  
Shashi Bhushan Tiwari ◽  
S. V. S. Narayana Murty ◽  
P. Ramesh Narayanan
Keyword(s):  
Failure Analysis ◽  
Launch Vehicle ◽  
Steel Ball ◽  
Actuator System ◽  
Satellite Launch Vehicle
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