Optimal explicit guidance of multistage launch vehicle along three-dimensional trajectory

Computationally Efficient Suboptimal Mid Course Guidance Using Model Predictive Static Programming (MPSP)

“…Next, dX N −2 can be expanded in terms of dX N −3 and dU N −3 and so on. Continuing the process initial k = 1, we can write 17th IFAC World Congress (IFAC'08) Seoul, Korea, July [6][7][8][9][10][11]2008…”

“…The idea of using optimal control techniques for the guidance of flight vehicles is not new ([3]- [6]). However, such a formulation leads to two point boundary value problems (TPBVP) [4].…”

A guidance algorithm for launch to equatorial orbit

“…In such cases, the problem of trajectory selection becomes one of trajectory optimization. The so‐called Linear Tangent Guidance Law or Linear Tangent Law (LTL) has been shown to correspond to optimal trajectories in special cases and to near optimal trajectories in many others (Battin, 1987; Sinha and Shrivastava, 1990). The guidance law proposed in this paper employs the LTL for the entire exoatmospheric part (Phase 2) of the flight.…”

An Explicit Reentry Guidance Law Using Bezier Curves

“…5) Inverse methods are of great interest in the context of synthesizing nonlinear autopilots [6][7][8] and guidance algorithms. [9][10][11][12][13] A survey about the inverse problem approach in optimal trajectory generation, both in Russia and in the United States, can be found in Yakimenko's paper. 3) In guidance applications, the variable guidance gains are correlated with the shape of the trajectory that will follow and satisfy particular terminal constraints.…”