Global and robust attitude control of a launch vehicle in exoatmospheric flight

Abstract The goal of this research is to design global and robust attitude control systems for launch vehicles in exoatmospheric flight. An attitude control system is global when it guarantees that the vehicle converges to the desired attitude regardless of its initial condition. Global controllers are important because when large angle maneuvers must be performed, it is simpler to use a single global controller than several local controllers patched together. In addition, the designed autopilots must be robust with respect to uncertainties in the parameters of the vehicle, which means that global convergence must be achieved despite of those uncertainties. Two designs are carried out. In the first one possible delays introduced by the actuator are neglected. The design is performed by using a Lyapunov approach, and the obtained autopilot is a standard proportional-derivative controller. In the second one, the effects of the actuator are considered. Then the design is based on robust backstepping which leads to a memory-less nonlinear feedback of attitude, attitude-rate, and of the engine deflection angle. Both autopilots are validated in a case study.

[1]  Panos J. Antsaklis,et al.  Linear Systems , 1997 .

[2]  Dennis S. Bernstein,et al.  Global stabilization of systems containing a double integrator using a saturated linear controller , 1999 .

[3]  H. Sussmann,et al.  On the stabilizability of multiple integrators by means of bounded feedback controls , 1991, [1991] Proceedings of the 30th IEEE Conference on Decision and Control.

[4]  Ashish Tewari.  Advanced Control Of Aircraft Spacecraft And Rockets , 2011 .

[5]  Guang Q. Xing,et al.  Design of a reduced order H∞ robust controller for an expendable launch vehicle in the presence of structured and unstructured parameter uncertainty , 1997 .

[6]  William T. O'Connor,et al.  Wave-based attitude control of spacecraft with fuel sloshing dynamics , 2015 .

[7]  Alberto Isidori,et al.  Nonlinear Control Systems II , 1999 .

[8]  Yasuhiro Morita,et al.  Design for robustness using the μ-synthesis applied to launcher attitude and vibration control , 2008 .

[9]  Ashish Tewari.  Basic Flight Mechanics , 2016 .

[10]  B. N. Suresh,et al.  Integrated Design for Space Transportation System , 2015 .

[11]  Zhong-Ping Jiang,et al.  Small-gain theorem for ISS systems and applications , 1994, Math. Control. Signals Syst..

[12]  Siddhartha Sen,et al.  Robust and fault tolerant controller for attitude control of a satellite launch vehicle , 2007 .

[13]  V. R. Lalithambika,et al.  Lyapunov based PD/PID in model reference adaptive control for satellite launch vehicle systems , 2016 .

[14]  Abdulrahman H. Bajodah,et al.  Robust launch vehicle’s generalized dynamic inversion attitude control , 2017 .

[15]  Caro Lucas,et al.  Aerospace launch vehicle control: an intelligent adaptive approach , 2006 .

[16]  Bei Lu,et al.  Switching robust control for a nanosatellite launch vehicle , 2015 .

[17]  Yuandan Lin,et al.  INPUT TO STATE STABILIZABILITY FOR PARAMETRIZED FAMILIES OF SYSTEMS , 1995 .

[18]  Karim Salahshoor,et al.  An indirect adaptive predictive control for the pitch channel autopilot of a flight system , 2015 .

[19]  Changchun Hua,et al.  Attitude control of reusable launch vehicle in reentry phase with input constraint via robust adaptive backstepping control , 2015 .