Authors
1 Faculty of Aerospace Engineering, Khajeh Nasir al-Din Tusi University of Technology, Tehran, Iran
2 Faculty of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran
Abstract
In this Paper, The online optimal integrated guidance and control algorithm design has been provided for two-stages Launch Vehicle .The flight equations are nonlinear and has been derived in flight plane. In order to solve it based on numerical solution and shooting method logic by the combination between ODE - start to end solver algorithm by considering initial conditions for integrated states and co-states - and optimization fmincon SQP algorithm has been acted. In order to verify designing method the results of this algorithm solutions has been compared with the results of a valid separated guidance and control algorithm for launch vehicle. The result function involves minimum control effort, terminal terms and minimizing burning time. The results indicate the satisfaction of three mentioned identities achieving high accurate orbital insertion and more coordination between the operation of guidance and control algorithms in integrated logic comparing with separated ones.
Keywords
- Menon, P.K., Sweriduk, G.D. and Ohlmeyer, E.J., Optimal Fixed- Interval Intergrated Guidance Control Laws for Hit- to – Kill Missile, AIAA; 2nd Edition, Vol. 157, 1994.
- Menon, P.K. and Ohlmeyer, E. J., “Nonlinear Integrated Guidance and Control Laws for Homing Missiles,” Presented at the AIAA Guide, Navigation Control Conference Exhibit, Montreal, Canada, 2001, AIAA paper 2001- 4160.
- Lin, C.F. and Yueh, W.R. “Optimal controller for Homing Missiles,” Journal of Guidance, Control and Dynamics, Vol. 8, No. 3, 1985.
- Evers, J.H., Cloutier, J.R., Lin, C.F., Yueh, W.R. and Wang, Q., “Application of Integrated Guidance and Control Schemes to a Precision Guided Missil,” American Control conference, 1992, pp. 3225 – 3230.
- Lin, C.F., Ohlmeyer, E., Bibel, E. and Malyevac, S., “Optimal Design of Intergrated Guidance Control,” Presented at the 1998 World Aviation Conference, 1998 AIAA- 985519
- Menon, P.K., Iragavarapu, V.R. and Ohlmeyer, E.J. “Intergrated Design of Agile Missile Guidance and Autopilot System,” Control Engineering Practice, 9, Issue 10, 2001, pp. 1095- 1106.
- K. Menon,E.J Ohlmeyer, “Integrated Design of Agile Missile Guidance and Control Systems,” AIAA Missile Since Conference, 1998, Monterey.CA.
- Palumbo, N.F. and Jackson, T.D., “Integrated Missile Guidance and Control: A State Dependent Riccati Differential Equation Approach,” IEEE International Conference on Control Application, 1999, pp.243-248.
- Jessick, M.V. and Knobbs, D.L., “Integrated Guidance and Control Algorithms for National Launch System,” AIAA Guidance, Navigation and Control Conference, August10-12/Hilton Head Island, SC.
- Lecture of Flight Dynamics of Launch Vehicle Professor Jafar Roshanian. Aerospace Engineering Faculty, K.N.Toosi University of Technology, Tehran, Iran.
- Kirk, D. E., Optimal Control Theory An Introduction, Prentice-Hell Inc., Englewood Cliffs New Jersey, 1970.
- Mathworks, Matlab Documentation, ODE Solvers, Fmincon Algorithm.
- Lecture of Launch Vehicle Design, Professor Mir Shams. Aerospace Engineering Faculty, K.N.Toosi University of Technology.
)