Guidance and control of a launch vehicle using a stochastic gradient projection method

A recently developed nonlinear programming stochastic projection of the gradient-type technique is applied to get and test novel procedures for tri-dimensional guidance and control of a satellite solid-fuel launch vehicle. Near optimal open-loop and low-frequency closed-loop solutions are obtained by parametrization of the control history and by considering the satisfaction of boundary constraints unless of specified random errors. Numerical simulations and tests show that the closed-loop solution can cope with the typical model uncertainties and environmental perturbations. A non standard situation of having a fourth stage with a free burning time is tested.

[1]  Philip E. Gill,et al.  Practical optimization , 1981 .

[2]  Frank J. Regan.  Re-entry vehicle dynamics , 1984 .

[3]  W. Williamson.  Use of Polynomial Approximations to Calculate Suboptimal Controls , 1971 .

[4]  M. Seetharama Bhat,et al.  An explicit closed-loop guidance for launch vehicles , 1991 .

[5]  Kurt Chudej,et al.  GUIDANCE AND TRAJECTORY OPTIMIZATION UNDER STATE CONSTRAINTS - APPLIED TO A SANGER - TYPE VEHICLE , 1993 .

[6]  C. Hargraves,et al.  DIRECT TRAJECTORY OPTIMIZATION USING NONLINEAR PROGRAMMING AND COLLOCATION , 1987 .

[7]  Anthony J. Calise,et al.  Rapid near-optimal aerospace plane trajectory generation and guidance , 1991 .

[8]  Steven N. Williams,et al.  Optimal low thrust trajectories using differential inclusion concepts , 1994 .

[9]  Jason L. Speyer,et al.  Techniques for Developing Approximate Optimal Advanced Launch System Guidance , 1991, 1991 American Control Conference.

[10]  Bruce A. Conway,et al.  Discrete approximations to optimal trajectories using direct transcription and nonlinear programming , 1992 .

[11]  S. K. Shrivastava,et al.  Optimal explicit guidance for three-dimensional launch trajectory , 1989 .

[12]  M. Psiaki,et al.  Parallel solver for trajectory optimization search directions , 1992 .

[13]  Kenneth D. Mease,et al.  Geometric synthesis of aerospace plane ascent guidance logic , 1994, Autom..

[14]  Srinivas R. Vadali,et al.  Trajectory optimization using parallel shooting method on parallel computer , 1995 .

[15]  J. Breakwell.  The Optimization of Trajectories , 1959 .

[16]  B. Conway,et al.  Optimization of low-thrust interplanetary trajectories using collocation and nonlinear programming , 1995 .

[17]  Albert Benveniste,et al.  The synchronous approach to reactive and real-time systems , 1991 .

[18]  Hans Seywald,et al.  Trajectory optimization based on differential inclusion , 1994 .

[19]  Ping Lu.  An inverse dynamics approach to trajectory optimization for an aerospace plane , 1992 .

[20]  A. Calise,et al.  Hybrid approach to near-optimal launch vehicle guidance , 1994 .

[21]  J. Betts,et al.  Trajectory optimization on a parallel processor , 1989 .

[22]  Fl. Richard,et al.  Open and closed loop guidance for an airbreathing winged launch vehicle , 1995 .

[23]  Anthony J. Calise,et al.  A Weak Hamiltonian Finite Element Method for Optimal Guidance of an Advanced Launch Vehicle , 1989, 1989 American Control Conference.

[24]  Gottfried Sachs,et al.  Optimal control of ascent trajectories and rotary dynamics for wingless orbital stages , 1991 .