"This is a long-overdue volume dedicated to space trajectory optimization. Interest in the subject has grown, as space missions of increasing levels of sophistication, complexity, and scientific return - hardly imaginable in the 1960s - have been designed and flown. Although the basic tools of optimization theory remain an accepted canon, there has been a revolution in the manner in which they are applied and in the development of numerical optimization. This volume purposely includes a variety of both analytical and numerical approaches to trajectory optimization. The choice of authors has been guided by the editor's intention to assemble the most expert and active researchers in the various specialties presented"--Provided by publisher. Read more... Cover -- Half-title -- Series title -- Title -- Copyright -- Contents -- Preface -- 1 Problem of Spacecraft Trajectory Optimization -- 1.1 Introduction -- 1.2 Solution Methods -- 1.2.1 Analytical Solutions -- 1.2.2 Numerical Solutions via Discretization -- 1.2.3 Evolutionary Algorithms -- 1.3 The Situation Today with Regard to Solving Optimal Control Problems -- 2 Primer Vector Theory and Applications -- 2.1 Introduction -- 2.2 First-Order Necessary Conditions -- 2.2.1 Optimal Constant-Specific-Impulse Trajectory -- 2.2.2 Optimal Impulsive Trajectory -- 2.2.3 Optimal Variable-Specific-Impulse Trajectory -- 2.3 Solution to the Primer Vector Equation -- 2.4 Application of Primer Vector Theory to an Optimal Impulsive Trajectory -- 2.4.1 Criterion for a Terminal Coast -- 2.4.2 Criterion for Addition of a Midcourse Impulse -- 2.4.3 Iteration on a Midcourse Impulse Position and Time -- 3 Spacecraft Trajectory Optimization -- 3.1 Introduction -- 3.2 Transcription Methods -- 3.2.1 A Basic Collocation Method (Using Hermite Polynomials) -- 3.2.2 Pseudospectral Methods -- 3.2.3 A Direct Method Not Using Collocation: R-K Parallel-Shooting -- 3.2.4 Comparison of Direct Transcription Methods -- 3.3 Selection of Coordinates -- 3.3.1 Motivation for Choice of Coordinate System -- 3.3.2 Coordinate Transformations -- 3.3.3 Interplanetary Trajectories -- 3.4 Modeling Propulsion Systems -- 3.4.1 Impulsive Thrust Case -- 3.4.2 Continuous Thrust Case -- 3.4.3 Power-Limited Case -- 3.5 Generating an Initial Guess -- 3.5.1 Using a Known Optimal Control Strategy -- 3.5.2 Shape-Based Methods for Generating Suboptimal Trajectories -- 3.5.3 Using Evolutionary Methods to Generate an Initial Guess -- 3.6 Computational Considerations -- 3.6.1 Equation Scaling -- 3.6.2 Grid Refinement -- 3.6.3 Other Grid Refinement Strategies -- 3.6.4 Solving Problems with Variables That Change with SignificantlyDifferent Timescales -- 3.7 Verifying Optimality -- 3.7.1 Optimality of Assumed Control Switching Structures and the DiscreteSwitch Function -- 3.7.2 Example: Two and Three Thrust-Arc Rendezvous -- 3.7.3 Verifying Optimality by Integration of the Euler-Lagrange Equations -- 4 Software for Spacecraft Trajectory Optimization -- 4.1 Introduction -- 4.2 Trajectory Model -- 4.3 Equations of Motion -- 4.4 Finite Burn Control Models -- 4.4.1 Thrust Vector Parameter Model -- 4.4.2 Thrust Vector Optimal Control Model -- 4.5 Solution Methods -- 4.5.1 Root Finding Problem: fobj = 0.0,mineq = 0,meq = n1 -- 4.5.2 Mini-Max Problem: fobj=0.0,mineq=0,meq1,n1 -- 4.5.3 Nonlinear Programming Problem: mineq0,0meq<n, n1 -- 4.6 Trajectory Design and Optimization Examples -- 4.6.1 Free-Return Lunar Flyby Mission -- 4.6.2 Lunar Orbiter and Lunar Impacter Mission -- 4.7 Concluding Remarks -- 5 Low-Thrust Trajectory Optimization -- 5.1 Introduction and Background -- 5.2 Low-Thrust Trajectory Optimization -- 5.2.1 Problem Statement -- 5.2.2 Thrust-Steering Control Laws -- 5.2.3 Analysis of the Control Laws -- 5.2.4 Solution Method -- 5.3 Numerical Results -- 5.3.1 Minimum-Time LEO-GEO Transfer -- 5.3.2 Minimum-Time GTO-GEO Transfer -- 5.3.3 Minimum-Propellant LEO-GEO Transfer -- 5.3.4 Minimum-Propellant LEO-GEO Transfer with Variable Isp -- 5.4 Conclusions -- 6 Optimal Low-Thrust Transfer in Circular Orbit -- 6.1 Introduction -- T$27708