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Luís Campos - One of the best experts on this subject based on the ideXlab platform.

  • On the Application of Special Functions to Non-Linear and Unsteady Stability: (Part I) Method of Iterative Solution of a Coupled Non-Linear System
    Integral Transforms and Special Functions, 2003
    Co-Authors: Luís Campos
    Abstract:

    A new approach to longitudinal airplane stability is presented ( \S 1), which is more general than the method of linear, constant stability derivatives, and allows oscillations which are non-sinusoidal and non-periodic, and amplitude growth or decay which is non-exponential. This approach to the solution of the non-linear, coupled Equations of longitudinal motion of an airplane ( \S 2.1), uses an iterative, cyclic method ( \S 2.2), as follows: (i) a constant flight path angle is assumed, and elimination between the two force balance Equations, gives airspeed as a function of distance along the flight path ( \S 2.3); (ii) this airspeed variation is fed into the Pitching Moment Equation, to specify an angle-of-attack oscillation with changing frequency ( \S 2.4); (iii) the flight path angle is calculated from the airspeed (i) and angle-of-attack (ii), to determine the deviation from the preceding iteration ( \S 4.1), and stop the cyclic process if the change is small (as discussed in Part II). The airspeed ...

J.b. Russell - One of the best experts on this subject based on the ideXlab platform.

  • 5 – Elementary treatment of Pitching motion
    Performance and Stability of Aircraft, 1996
    Co-Authors: J.b. Russell
    Abstract:

    This chapter discusses the behavior of an aircraft in pitch. Although the aircraft moving in pitch is considered, the effects of inertia and unsteady aerodynamics are neglected. The purpose of the chapter is to determine such things, as the elevator angles and stick forces required for steady flight as a function of the properties of the aircraft. Also, it aims to consider the static stability of the aircraft. To do this, an Equation is required relating the Pitching Moment to such quantities as speed, elevator angle and cg position. In some sense, the aircraft behavior in pitch is modeled and the resulting Equation is known as the “Pitching Moment Equation” of the aircraft. The reader is reminded of the general assumptions given in the first chapter of the book, to which is added that of symmetric flight, i.e., there is no sideslip. It also explains concepts related to Pitching Moment characteristics of a wing. The certain actions that a pilot needs to perform to change speed are also covered here.

M.v. Cook - One of the best experts on this subject based on the ideXlab platform.

  • Chapter 8 – Manoeuvrability
    Flight Dynamic Principles, 2007
    Co-Authors: M.v. Cook
    Abstract:

    Publisher Summary This chapter discusses manoeuvrability in relation to aeroplanes. The first section introduces the concept of manoeuvrability and defines a manoeuvring flight. It is sometimes called accelerated flight and is defined as the condition when the airframe is subject to temporary, or transient, out of trim linear and angular accelerations resulting from the displacement of the controls relative to their trim settings. In analytical terms, the manoeuvre is regarded as an increment in steady motion, over and above the initial trim state, in response to an increment in control angle. Today, considerations of manoeuvrability in the context of aircraft handling have moved on from the simple analysis of normal acceleration response to controls alone. The second section discusses about the steady pull-up maoeuvre and the third explains the Pitching Moment Equation. Then the fourth section explores the longitudinal manoeuvre stability. Finally, the aircraft dynamics and manoeuvrability are explored in the last section of the chapter. The static, manoeuvre and dynamic stability and control characteristics of an aeroplane are really very much inter-related and should not be treated entirely as isolated topics.