By Franklin, James A.
This article offers the rules of dynamics and keep watch over for vertical and brief take-off and touchdown (V/STOL) plane. the 1st e-book of its style, it truly is meant for graduate scholars and execs in aeronautics who've wisdom of linear structures research, plane static, and dynamic balance and regulate. The textual content starts with a dialogue of V/STOL plane operations, relocating directly to keep an eye on suggestions, equations of movement, longitudinal and lateral-directional flying characteristics in either hover and ahead flight, wind and turbulence responses, and regulate augmentation and cockpit screens. particular examples of the YAV-8B Harrier and XV-15 Tilt Rotor plane are used to demonstrate real V/STOL dynamic and regulate features.
- information and knowledge showing during this booklet are for informational reasons simply. AIAA and the writer should not answerable for any harm or harm because of use or reliance, nor do AIAA and the writer warrant that use or reliance could be unfastened from privately owned rights.
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Additional info for Dynamics, Control, and Flying Qualities of V/STOL Aircraft
Example text
2 : 1 '5> CO I . 1 1 Frequency, rad/sec a) Without pilot lead. Fig. 10 Root locus and Bode plots of bank-angle control. 8 NASA/Army XV-15. 4 Equations of Motion for Hover and Forward Flight Before beginning the discussion of V/STOL aircraft flying qualities, it is appropriate to review the equations of motion for hover and forward flight. The aircraft axis system on which the forces, moments, and linear and angular velo cities of the equations of motion are based is shown in Fig. 1. It is a righthand system originating at the center of gravity of the aircraft with the longitudi nal or χ axis pointing forward out the nose, the lateral or y axis pointing out the right wing, and the vertical or ζ axis pointing downward.
The instability of the complex pair is somewhat reduced compared to the case in which M is zero. The XV-15 Tilt Rotor provides a contrasting example for hover characteris tic roots. 34) ] = 0 The principal differences from the Harrier are in the increased level of pitch and heave damping and the positive value of M which produces the more stable real roots. The unstable complex pair is still evident and is a conse quence of the positive pitching moment caused by forward velocity. Root locus plots are useful in visualizing how characteristics of the aircraft influence the characteristic roots.
These simplifications are based on the assumptions that the aircraft is in wings-level flight and that it has symme try about the x-z plane. These assumptions are reasonable for fixed-wing aircraft and, in some instances (though only infrequently), for rotary-wing vehi cles. Notice also the absence of terms on the left-hand side, like and Z^, whose presence can only rarely be justified by fluid physics. Terms such as Y and Y are frequently ignored as well, and in some cases L and Ν , particularly near hover, are also neglected.