Analysis of Optimal Booster Ascent Trajectories

Sarita Kinney

Master of Science, May 1995

ABSTRACT

Scientists at Honeywell Technology Center (HTC) worked several years on developing a computationally-efficient, real-time trajectory optimization and guidance approach for future launch vehicles. Approximate solution methods suitable for onboard guidance were developed for the ascent-to-orbit problem. Recommendations for further work suggested investigating other methods that may be more efficient and adaptable.

As a student intern at HTC for six months, under the guidance of Dr. Blaise Morton, I investigated another solution method suitable for onboard guidance. In this paper, I present trajectory analysis for a booster vehicle to describe an efficient guidance algorithm concept, suitable for real-time in-flight trajectory computation. The algorithm computes in-flight, minimum-fuel trajectories from the vehicle's position at staging to its final destination. An approximate iterative solution is developed for computing the optimal control parameters, using Newton's Method, suggested by Dr. Morton, to solve the nonlinear inverse function problem. A two-dimensional, flat earth, standard point mass vertical plane model is employed.

The subject matter of this paper requires a basic understanding of the optimal guidance of a booster vehicle and its mission sequence.

Research supported by the Minnesota Center for Industrial Mathematics (MCIM)