Cover page and Table of Contents: PDF (size: 187KB)
Full Text (PDF, 187KB), PP.53-60
Views: 0 Downloads: 0
Small solid launcher, dynamic modeling, simulation, optimization, filter design, SDRE-FOS autopilot
The dynamics of a small solid launch vehicle has been investigated. This launcher consists of a liquid upper stage and three fundamental solid rocket boosters aligned in series. During the ascent flight phase, lateral jets and grid fins are adopted by the flight control system to stable the attitude of the launcher. The launcher is a slender and aerodynamically unstable vehicle with sloshing tanks. A complete set of six-degrees-of-freedom dynamic models of the launcher, incorporation its rigid body, aerodynamics, gravity, sloshing, mass change, actuator, and elastic body, is developed. Dynamic analysis results of the structural modes and the bifurcation locus are calculated on the basis of the presented models. This complete set of dynamic models is used in flight control system design. A methodology for employing numerical optimization to develop the attitude filters is presented. The design objectives include attitude tracking accuracy and robust stability with respect to rigid body dynamics, propellant slosh, and flex. Later a control approach is presented for flight control system of the launcher using both State Dependent Riccati Equation (SDRE) method and Fast Output Sampling (FOS) technique. The dynamics and kinematics for attitude stable problem are of typical nonlinear character. SDRE technique has been well applied to this kind of highly nonlinear control problems. But in practice the system states needed in the SDRE method are sometimes difficult to obtain. FOS method, which makes use of only the output samples, is combined with SDRE to accommodate the incomplete system state information. Thus, the control approach is more practical and easy to implement. The resulting autopilot can provide stable control systems for the vehicle.
Ping Sun, "Solid Launcher Dynamical Analysis and Autopilot Design", IJIGSP, vol.3, no.1, pp.53-60, 2011. DOI: 10.5815/ijigsp.2011.01.08
J. P. B. Vreeburg, Dynamics and Control of a Spacecraft with a Moving Pulsating Ball in a Spherical Cavity, Acta Astronautica, 40(2), 1997, 257-274.
B. Clement, G. Duc, & S. Mauffrey, Aerospace launch vehicle control: a gain scheduling approach, Control Engineering Practice, 13(1), 2003, 333-347.
A. R. Mehrabian, C. Lucas, & J. Roshanian, Aerospace launch vehicle control: an intelligent adaptive approach, Aerospace Science Technology, 10(1), 2006, 149-155.
R. P. Patera, Application of symmetrized covariances in space confliction prediction, Advances In Space Research, 34(1), 2004, 1115-1119.
D. A. Cicci, C. Qualls, & G. Landingham, Two-Body Missile Separation Dynamics, Applied Mathematics And Computation, 198 (1), 2008, 44-58.
C. Carnevale, & P. D. Resta, Vega Electromechanical Thrust Vector Control Development. Proc. 43sd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cincinnati, OH, 2007, AIAA 2007-5812.
M. R. Malik, Analysis of Crossflow Transition Flight Experiment aboard the Pegasus Launch Vehicle. Proc. 37th AIAA Fluid Dynamics Conference and Exhibit, Miami, FL, 2007, 2007-4487.
H. Li, X. Jing, & W. Zhuang, Study On Simulation Of Launch Vehicle Attitude Control System. Proc. IEEE International Conference on Mechatronics & Automation, Niagara Falls, Canada, 2005, 2022-2025.
W. Du, B. Wie, & M. Whorton, Dynamic Modeling and Flight Control Simulation of a Large Flexible Launch Vehicle. Proc. Guidance, Navigation and Control Conference and Exhibit, Honolulu, Havaii, 2008, AIAA 2008-6620.
H. Mori, Control System Design of Flexible-Body Launch Vehicles, Control Engineering Practice, 7(1), 1999, 1163-1175.
A. Shekhawat, C. Nichkawde, & N. Ananthkrishnan, Modeling and Stability Analysis of Coupled Slosh-Vehicle Dynamics in Planar Atmospheric Flight. Proc. 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 2006, AIAA 2006-427.
E. de Weerdt, E. van Kampen, & D. van Gemert, etc., Adaptive Nonlinear Dynamic Inversion for Spacecraft Attitude Control with Fuel Sloshing. Proc. Guidance, Navigation and Control Conference and Exhibit, Honolulu, Havaii, 2008, AIAA 2008-7162.
James R Cloutier, State dependent Riccati equation techniques: an overview, Proceedings of American Control Conference, Albuquerque, New Mexico, 20-23 June, 1997, Vol. 1, pp. 932-934.
W Luo and Y C chu, Attitude control using the SDRE techque. Proceedings of 7th International Conference on Control, Automation, Robotics and Vision, Singapore, 12-15, December, 2002, Vol. 1, pp. 1281-1285.
S Oberoi, S Janardhanan and B Bandyopadhyay, Output feedback control of practical launch vehicle systems, Proceedings of IEEE International Conference on Control Applications, Taipei, Taiwan, 14-16 September 2004, Vol. 1, pp. 14-15.
D K Parrish and D B Ridgely, Attitude control of a satellite using the SDRE method, Proceedings of American Control Conference, Albuquerque, New Mexico, 20-23 June, 1997, Vol. 1, pp. 942-943.
M C Saaj and B Bandyopadhyay, A new algorithm for discrete-time sliding-mode control using fast output sampling feedback, IEEE Transactions on Industrial Electronics, Vol. 49, No. 3, June 2002, pp. 518-519.
M Xin and S N Balakrishnan, State dependent Riccati equation based spacecraft attitude control, Proceedings of 40th AIAA Aerospace Sciences Meeting & Exhibit, Reno, NV, 23-25, January, 2002, Vol. 1, pp. 2-3.
P K Menon and G D Sweriduk, Nonlinear discrete-time design methods for missile flight control systems, Proceedings of AIAA Guidance, Navigation and Control Conference, Providence, RI, 16-19 August, 2004, pp. 952-968.