This work presents the open-loop stability analysis and an active control strategy for an airbreathing hypersonic vehicle. The 14-XB, a bidimensional flow airframe derived from the Brazilian 14-X Aerospace Hypersonic Vehicle, is adopted as study platform. In order to perform such analyses, a simulation mathematical model of the airframe longitudinal forces and moments is obtained using perfect gas equations, after considering the relevance of the real gas hypotheses for the expected Mach number range and verifying that the simpler formulation is sufficient. An all-moving horizontal tail is designed in order to enable the aircraft trimming. The horizontal tail design considered simple constraints based on static analysis, and the same gas equations as those used for the airframe study. In order to analyze the aircraft';s dynamic behavior, a Six-Degree-of-Freedom set of equations of motion considering a spherical, rotating Earth is presented in detail, and the necessary conditions to have adequate longitudinal trimming in this scenario are discussed. The open-loop stability of the 14-XB with the designed horizontal tail is assessed through eigenvalue analysis and numerical flight simulations with the horizontal tail fixed at a trim position. Having observed that the aircraft presents unstable long-term natural modes, an active control strategy is suggested in order to stabilize the vehicle and track a desired flight path angle, assuming that thrust is constant and the control surface is an all-moving horizontal tail. The suggested control structure presents pitch stability augmentation system and flight path angle compensator. Optimal gains are calculated using linear quadratic design, along with a gain-scheduling strategy based on simultaneous control design, and the resulting controller presents proper results.

Este trabalho tem como objetivo o estudo, implementação e validação de métodos semi-empíricos utilizados para estimar as derivadas de estabilidade estáticas longitudinais de uma aeronave regional ainda em sua fase de anteprojeto. Estas derivadas são importantes para se avaliar as características de estabilidade e controle de uma aeronave. Para isso, foi elaborado um código computacional, desenvolvido em linguagem Matlab, tendo como base para o cálculo das derivadas a metodologia ESDU. Nos pontos onde esta metodologia não apresentou exatidão, dois outros procedimentos de cálculo foram utilizados, desenvolvidos: (i) pelo Prof. Dr. Jan Roskam e (ii) pela NASA, relatado no NASA TND-6800. A geometria da aeronave é inserida como dados de entrada do programa/código, que calcula as derivadas considerando a contribuição de cada componente da aeronave e efeitos aerodinâmicos. Os resultados obtidos são comparados a resultados experimentais provenientes de ensaio em túnel de vento, com o objetivo de validar a metodologia.