文档介绍：Fundamentals of Airplane Flight Mechanics
Preface
Flight mechanics is the application of Newton’s laws (F=ma and M=Iα) to
the study of vehicle trajectories (performance), stability, and aerodynamic
control. There are two basic problems in airplane flight mechanics: (1) given
an airplane what are its performance, stability, and control characteristics?
and (2) given performance, stability, and control characteristics, what is the
airplane? The latter is called airplane sizing and is based on the definition
of a standard mission profile. mercial airplanes including business
jets, the mission legs are take-off, climb, cruise, descent, and landing. For a
military airplane additional legs are the supersonic dash, fuel for bat,
and specific excess power. This text is concerned with the first problem, but
anization is motivated by the structure of the second problem. Tra-
jectory analysis is used to derive formulas and/or algorithms puting
the distance, time, and fuel along each mission leg. In the sizing process, all
airplanes are required to be statically stable. While dynamic stability is not
required in the sizing process, the linearized equations of motion are used in
the design of automatic flight control systems.
This text is primarily concerned with analytical solutions of airplane flight
mechanics problems. Its design is based on the precepts that there is only one
semester available for the teaching of airplane flight mechanics and that it is
important to cover both trajectory analysis and stability and control in this
course. To include the fundamentals of both topics, the text is limited mainly
to flight in a vertical plane. This is not very restrictive because, with the
exception of turns, the basic trajectory segments of both mission profiles and
the stability calculations are in the vertical plane. At the University of Texas
at Austin, this course is preceded by courses on low-speed aerodynamics and
linear system theory. It is followed by a