Trajectories of Launch and Reentry Systems

This book examines ascent trajectories of space launch vehicles and re-entry trajectories of space capsules. The decommissioned SCOUT is used as a reference launcher and the reader will be introduced to various and detailed aspects of a launch vehicle that are not generally available in the literature, since this information is limited to internal industry and agency reports. The SCOUT data are used here as a study case and the reader will be able to generate a complete numerical code using the general equations of flight introduced in different reference systems, including the time-dependent parameters representing the launcher and its environment with a high degree of accuracy. The guidance parameters for injection into orbits of different semiaxes, eccentricities and inclinations are determined by guessed values obtained by original analytical formulae. These formulae allow a fast and sufficiently accurate design of the rocket trajectory within the atmosphere; in the exo-atmospheric flight closed form solutions of the optimal problem of injection into orbit are provided.

The second part of the book deals with re-entry trajectories. Basic analytical formulae for ballistic reentry are presented to evaluate the reentry trajectory and the capsule design in terms of critical parameters such as temperature and load peak. Entry corridors for ballistic reentry trajectories are then determined for various planets with atmospheres. The effect of lift is analysed to increase the entry corridors and guide the capsule to a target landing point. Autonomous and real-time guidance algorithms are developed for capsule of low aerodynamic efficiency and winged re-entry vehicles.

Appeals to graduate students in aerospace engineering and professionals in the aerospace sector Features numerous chapter-wise numerical examples and exercises (with solutions) Provides comprehensive analysis of the ascent rocket trajectory & accurate description of space launch systems

Autorentext

Paolo Teofilatto is professor of Flight Mechanics at Sapienza University of Rome, Italy, where he also served as dean of the School of Aerospace Engineering. He serves as full member of the International Academy of Astronautics (IAA), the Italian Space Agency, the Gran Sasso Scientific Institute Foundation, and the Italian Air Force Study Centre. He was responsible for the design, manufacture and launch of the Tigrisat and Stecco microsatellites, launched in 2014 and 2022 respectively.

Inhalt

Launch systems.- Ascent trajectories: atmospheric arc.- Ascent trajectories: exo-atmospheric arc.- Reentry Trajectories.- Appendix 1: Necessary conditions for optimal space trajectory.- Appendix 2: Solutions of the exercises.