Closed-form solutions for flight vehicles with high thrust angle

摘要

The present work deals with an analytical model for any flight vehicle (e.g., aircraft, rocket, and aerospace plane) with high thrust angle. This work produces closed-form solutions of two (aerodynamic and thrust) nonlinear feed- back controls, heart rate, and heat load; and integrates most of the state variables for flight vehicles. The analytical solutions require pairs of equality constant constraints.