مثبت (طيران)
مراجع

↑  Empennage - D. Stinton The design of the aeroplane, Longitudinal stability - Hoerner Fluid Dynamic Lift - Ilan Kroo, Aircraft Design. In stability considerations (tail sizing, tail area, stabiliser volume coefficient), authors always deal with the whole unit, that includes elevators. "Horizontal tail" or "tail" terms are generally used in lieu of "stabilizer".
↑  Roskam، Jan (2002). Airplane Design: Pt. 3. Lawrence: DARcorporation. ص. 287. ISBN:1-884885-56-X. مؤرشف من الأصل في 2022-07-06. اطلع عليه بتاريخ 2015-07-30.
↑  Daroll Stinton, The design of the aeroplane, "Longitudinal balance (trim)".
↑  Phillips، Warren F. (2010). "4.1 Fundamentals of Static Equilibrium and Stability". Mechanics of Flight (ط. 2nd). Hoboken, New Jersey: Wiley & Sons. ص. 377. ISBN:978-0-470-53975-0. When the controls are set so that the resultant forces and the moments about the center of gravity are all zero, the aircraft is said to be in trim, which simply means static equilibrium
↑  W.H. Phillips, A Career at NASA Langley Research Center, Chap.4, Flying Qualities
↑  Phillips، Warren F. (2010). "4.2 Pitch Stability of a Cambered Wing". Mechanics of Flight (ط. 2nd). Hoboken, New Jersey: Wiley & Sons. ص. 381. ISBN:978-0-470-53975-0. For an airplane to be statically stable in rotation, any disturbances in roll, pitch or yaw must all result in the production of a restoring moment that will return the aircraft to the original equilibrium state.
↑  Phillips، Warren F. (2010). "4.3 Simplified Pitch Stability Analysis for a Wing-Tail Combination". Mechanics of Flight (ط. 2nd). Hoboken, New Jersey: Wiley & Sons. ص. 391. ISBN:978-0-470-53975-0.
↑  "Horizontal stabilizer - elevator"، The Beginner's Guide to Aeronautics، NASA Glenn Research Center، 13 سبتمبر 2010، مؤرشف من الأصل في 2022-07-03
↑  Gérard Hartmann (12 مايو 2003)، "Les hydros Farman" (PDF)، Dossiers historiques et technique aéronautique française، مؤرشف من الأصل (PDF) في 2022-03-31، le stabilisateur avant sera supprimé en cours d'année ("the front stabilizer will be removed during the year")
↑  Gabriel Voisin, Mes 10.000 cerfs-volants (My 10,000 kites), page 166: "et je m'apprêtais à tirer sur mon équilibreur... puis il braqua son équilibreur vers la montée."
↑  Garrison, P; "Three's Company"; Flying 129 (12), December 2002, pp.85-86: "the stabilizer in the front" ... "This is the function of the stabilizer. if it's in the back it typically pushes downward, and if it's in the front it lifts upward." نسخة محفوظة 2014-05-23 على موقع واي باك مشين.
↑  Benson, T (Ed): "Airplane parts and functions"، Beginner's Guide to Aeronautics، NASA Glenn Research Center، مؤرشف من الأصل في 2022-05-31، On the Wright brother's first aircraft, the horizontal stabilizer was placed in front of the wings.
↑  US Patent US 6064923 A, Aircraft with reduced wing structure loading: "...a front stabilizer, generally known as a canard stabilizer," نسخة محفوظة 2017-01-16 على موقع واي باك مشين.
↑  "Parts of Airplane"، The Beginner's Guide to Aeronautics، NASA Glenn Research Center، مؤرشف من الأصل في 2022-03-24
↑  Horizontal stabilizer - elevator، NASA، مؤرشف من الأصل في 2022-07-03، On some aircraft, the pitch stability and control is provided by a horizontal surface placed forward of the center of gravity
↑  e.g. In AIR International May 1999, p.311, Hoerner and Borst, Fluid Dynamic Lift, page 11-29, and Page 11-33 Delta canard, NASA TM 88354, A look at handling qualities of canard configurations, p. 14 and Kundu, Aircraft Design, Page 92,
↑  Phillips، Warren F. (2010). "4.6 Simplified Pitch Stability Analysis for a Wing-Canard Combination". Mechanics of Flight (ط. 2nd). Hoboken, New Jersey: Wiley & Sons. ص. 425. ISBN:978-0-470-53975-0. …it is the main wing and not the canard that provides stability for the wing-canard configuration.
↑  AIAA/AHS/ASEE Aircraft Design, Systems and Operations Meeting: ... - Volume 2 - Page 309, "Pitching-moment results show the stabilising effect of the wing and the destabilizing effect of the canard."
↑  F.H. Nichols,The Effects of Wing Vertical Location and Vertical-tail Arrangement on the Stability Characteristics of Canard Airplane Configurations, page 9, "The body also produces a substantial destabilizing component which is adequately balanced by the large stabilizing effect of the wing."
↑  The X-29 ... while its canards — horizontal stabilizers to control pitch — were in front of the wings instead of on the tail"
↑  Theory and Practice of Using Flying Wings, Apogee Components نسخة محفوظة 2022-01-23 على موقع واي باك مشين.
↑  Notes on the stability and control of tailless airplanes, Jones, Robert, naca-tn-837, 1941 نسخة محفوظة 2020-12-02 على موقع واي باك مشين.
↑  Daroll Stinton, The design of the aeroplane, lateral and directional stability and spinning
↑  Barnard، R.H.؛ Philpott، D.R. (2010). "10. Aircraft control". Aircraft Flight (ط. 4th). Harlow, England: Prentice Hall. ص. 271. ISBN:978-0-273-73098-9.
↑  Barber, Horatio، "Chapter II - Stability and Control"، The Aeroplane Speaks، Electronic Text Center, University of Virginia Library، مؤرشف من الأصل في 2021-06-09
↑  Phillips، Warren F. (2010). "5 Lateral Static Stability and Trim". Mechanics of Flight (ط. 2nd). Hoboken, New Jersey: Wiley & Sons. ISBN:978-0-470-53975-0.
↑  Sweetman، Bill (2005). Lockheed Stealth. North Branch, Minnesota: Zenith Imprint. ص. 73. ISBN:0-7603-1940-5.
1 2 3  Raymer، Daniel P. (1999). "4.5 Tail Geometry and Arrangement". Aircraft Design: A Conceptual Approach (ط. 3rd). Reston, Virginia: American Institute of Aeronautics and Astronautics. ص. 78. ISBN:1-56347-281-3.
↑  Phillips، Warren F. (2010). "5.5 Effects of Tail Dihedral on Yaw Stability". Mechanics of Flight (ط. 2nd). Hoboken, New Jersey: Wiley & Sons. ص. 533. ISBN:978-0-470-53975-0.
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