• "Motion of a Vehicle in the Transition Region of the Restricted Three Body Problem (Summary)," • "Some Qualitative Characteristics of Near-Lunar Satellite Orbits," • "Orbit Determination for Stationary Satellites," • "Orbit Computation for Motion in a Non-Central Force Field," • "A Parameter Optimization Procedure for Multi-Stage Vehicles," • "A Combination Numerical-Analytical Approach to Ascent Trajectory Optimization," • "Asymptotic Matching in Power-Limited Interplanetary Transfers," • "Optimization Problems Caused by Interaction of Guidance and Propellant System," • "An Accelerated Gradient Method for Parameter Optimization with Nonlinear Constraints," • "Minimum-Fuel Transfers Between Coaxial Orbits, Both Coplanar and Noncoplanar," • "An Analytic Investigation of the Escape Problem Using Tangential Thrust," • "The Exact Analytic Solution of the Lunar Landing Problem," • "Geometric Constraints of the Disorbit Problem," • "Interplanetary Trajectory Analysis for Combined High and Low-Thrust Propulsion Systems," • "An Approximate Method for Predicting Lunary Satellite Lifetimes and Its Application to a Lunary Orbit Mission Analysis," • "Lunar Surface Accessibility for Manned Missions, 1968-1988," • "Determination of Orbital Rendezvous Requirements: Second Order Improvement." • “Aeroballistics Internal Note #30: Maximum Range of a Projectile in a Vaccuum,” • “Aeroballistics Internal Note #32: Differential Corrections in Plane of Flight. Derivation of System Equations,” • “Aeroballistics Internal Note No. 18: Differential Corrections Lateral to Plane of Flight. Prepatory Formulas and Data,” • “Aeroballistics Memo #51: Angle Relationships in Vacuum Flight Trajectories,” • “Aeroballistics Memo #47: A Method of Least Square Curve Fitting Using Orthogonal Polynomials,” • “Aeroballistics Memo #43: Second Order Linear Differential Equations with Slowly Varying Coefficients,” • Aeroballistics Internal Note #71: A Two-Component Inertial Guidance System in Three-Dimensional Space • Aeroballistics Internal Note #45: A New Type Correction Computer for the Redstone Range-guidance System • Aeroballistics Internal Note No. 37: Discussion of Systemic Errors to be Expected for Two Different Versions of a Two-Component System and Compilation of Various Numerical Constants Required for the Design of These Systems • Aeroballistics Internal Note #28: Choice of the Measuring Direction for the Redstone Missile on Long Range to Minimize Errors in the Guidance Function • Aeroballistics Memorandum #106: A Preliminary Study of Inertial Guidance for the Redstone Missile on the 98 Kilometer Range • Aeroballistics Memorandum #102: A Preliminary Study of Internal Guidance for the Redstone Missile on the 30-Mile Range • Aeroballistics Memorandum #95: A Preliminary Study of Inertial Guidance for the Redstone Missile on Short Ranges • Aeroballistics Memorandum #82: Influence of Control Equation Upon Guidance During the Dive Phase • Aeroballistics Internal Note No. 1: Selection of the Measuring Direction for a One Component Inertial Guidance System • Aeroballistics Memorandum #79: A One Component Inertial Guidance System (Third Study) • Aeroballistics Memorandum #66: Guidance Control Equation Coefficient Study • Aeroballistics Memo #29: Study of One Component Inertial Guidance during Free Flight