Printing stabilising vanes for aircraft

0001The invention relates to a to a pivot for tail Aircraft according to the preamble of claim 1. Such a stabilizer is known from US-A-3,971,535 is known. Tilt control surfaces are predominantly in the form of Ducks wings used to determine the controllability of aircraft, in particular to increase with delta wings. at Supersonic aircraft has the canard a large Speed ​​range to show a sufficient effect, therefore, the aim is this variable with a form geometry. Such a solution is through the Aircraft Tupolev Tu-144 became known. Here is the Canards of two halves, which in each case within a the hull arranged vertical axis between a fully swung out and a pivoted position wherein are formed. This solution brings namely towards a rigid canards significant aerodynamic advantages, which However, the expense of a considerable weight penalty. Thus the pivot bearings in question must be very large absorb bending moments, which of a significant increase Baugewichts leads.

0002Accordingly, the invention addresses the problem of providing a form generic pivoting stabilizer such that a significant simplification of the mechanical complexity and the Baugewichtes results.

0003This object is in a generic swing tail by the characterizing features of claim 1 dissolved.

0004It is particularly advantageous that the desired aerodynamic advantages of relatively low mechanical Effort be achieved. In addition, it is advantageous that the Swivel tail for movement of aircraft on the ground in Airport area can be swiveled so that Collisions with airport-side boarding facilities be more easily avoided.

0005Advantageous further developments of the invention are in the dependent claims indicated.

0006The invention is illustrated with reference to the drawing and closer explained. Show it<dl tsize="6"><dt>Fig. 1</dt><dd>an aircraft with a tail swing in full extended position,</dd><dt>FIG. 2</dt><dd>the plane to Fig.1 with the extended half Swing tail,</dd><dt>Fig. 3</dt><dd>the plane to Fig.2 with fully retracted Panning and empennage</dd><dt>Fig. 4</dt><dd>schematically shows a side view of the aircraft by Fig.1.</dd></dl>

0007Figure 1 shows an aircraft 1 with a fuselage 2, a Delta wing 3 and a pivoting tail 4 of the invention. Here, the invention consists therein that the Swivel tail 4 formed as a so-called oblique wings is. This wing is integrally formed and has approximately at its center a pivot point, in which he to an approximately vertical axis 5 is pivotable. The image shows the pivoting stabilizer 4 in the fully extended position, in which he maximum effect at low speeds, shows. This configuration is advantageous when starting and Landing.

0008Figure 2 shows the aircraft 1 with oblique gestelltem Swivel tail 4. In this position, the effective reduced range of the swing tail. In addition, the Tail now a sweep on. This configuration is advantageously in cruise flight at transonic Speeds.

0009Figure 3 shows the aircraft 1 with fully retracted Swivel tail 4. In this position the pivot tail is brought in the transition to supersonic, since in this Speed ​​range, the effect of the swing tail 4 is not needed. For movements of aircraft on the ground reduces swiveled tail risk of Collisions with airport-side boarding facilities.

0010The use of the swing tail inventive not limited to use as a canard. There are also aircraft configurations possible, the Swivel tail is used as a tail unit. In Figure 3 is indicated schematically, such a tail unit 6th

0011Figure 4 shows the above aircraft with the fuselage 2 and the Swivel tail 4 schematically in a side view. Here appears the pivot axis 5 in the image plane. One notices, that the pivot axis 5 relative to the vertical V forward is inclined. This measure can aerodynamic Asymmetries caused by the pivoting motion, be compensated. The Vertical V is in level flight perpendicular to the flight axis.

0012A further measure to aerodynamic asymmetries, which caused by the pivoting movement, balance is therein, that the pivot axle outside the vertical Plane of symmetry of the aircraft lies. See also Swivel axis 5a and symmetry plane 7 in Figure 3.

0013The static advantages of a one-piece oblique wing result from the fact that this as a static point a continuous beam deflection acts. Thereby, the Pivot not burdened by forces off Bending moments arise. Further advantages, particularly in With regard to the kinematics are achieved in that the Swivel mechanism has only one pivot bearing. this leads to to a simple structure of light weight. In addition to the operation of the invention Swivel tail only small driving forces required.

0014An embodiment of the invention is that the Swivel tail control surfaces in the form of conventional control valves having.

0015A further embodiment of the invention is that the pivoting tail for tax purposes about its longitudinal axis is designed to pivot. Allows the setting angle the pivoting stabilizer be changed.

0016The invention opens up a pivot unswept tail the possibility to realize pivoting tail, which in its fully extended position over recent Solutions have greater spans and dilations. In order to , larger stabilizer forces are generated as with the recent duck wings, the result of their Delta form only a have low elongation. Considering the growing Importance of starting power, especially with regard to the Noise, is a second generation of Supersonic airliners not unlike the Concorde without the help of lift flaps on the wing for take-off and Landing commented. Because these flaps with a delta wing in a large distance from the center of gravity of the aircraft are arranged long tail moments are required to balance the moments created by these flaps. The Empennage invention permits the production such large tail moments in a highly cost-effective Wise.