DE2202415A1 - VTOL or V / STOL aircraft - Google Patents

Description

EIKENBERG & BRÜMMERSTEDT

PATENT LAWYERS IN HANOVER

HAWKER SIDDELEI AVIAIION LIMITED 240/526

VTOL or V / STOL aircraft

The invention "relates to a vertical take-off aircraft (VTOL) or a plug-in item for vertical / short-range take-off and landing (V / STOL) with thrust deflection at the outlet of the jet pipe or the engine cowling, &, i.e., a plug-in item in which a part or the entire vertical '. pusher and the plug attitude control by deflecting the SCHUMANN! bes a forward driving engine is obtained.

The invention is based on the object of creating a thrust deflection system for such plug-in items that is simple

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is under construction, offers versatile control options and is geometrical as well as being aerodynamically adapted to the conditions of the plug stuff.

You set task is according to the invention thereby ^! solved that at least two independently rotatable in the direction of the forward thrust deflection elements are provided, j through which the normal gas flow can be deflected in a vertical or almost vertical direction and then through one or more openings in the jet pipe or in the engine cowling 'is discharged that are automatically released when the elements are rotated.

The deflection elements can in their non-rotated position form upper and lower end parts of the engine cowling, each part being double-walled and the profiles of the walls are determined externally by aerodynamic aspects and internally by the requirements of the flow of the engine exhaust gases. The deflection elements are rotatably arranged on transverse bearings attached to the engine cowling. The deflection elements can also be designed and arranged so that they are in the profiles during normal cruise the engine cowling are stowed away and in this position the openings for the vertical thrust are smooth surfaces bridge.

Separate actuation devices for each deflection element allow a combined or differential adjustment of the deflection elements, so that different thrust variations are possible.

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are adjustable. The simultaneous adjustment "of both actuators to the rear leads to a symmetrical rotation of the deflection elements in the thrust direction of the engine, and the deflected thrust is directed evenly up and down, so that if necessary there is a possibility for an instantaneous End of the buoyancy is given.

From this position, a constant differential movement of the actuating devices can be initiated, as a result of which a combined rotation of the deflecting elements clockwise or counterclockwise is achieved in positions in which the total engine thrust either up or down is diverted.

It can also be seen that with a SIOL or YTOL plug-in tool, by gradually adjusting or modulating the deflecting elements, a gradual transition from vertical to forward thrust is possible without adjusting the engine throttle valve, the response level thus obtained being independent of the response of the engine.

For engines located at the rear of the fuselage and on opposite sides of the fuselage, the application of upward and downward diverted thrust causes
the forward propulsion engines exert a strong roll moment on the plug stuff. Since in the event of a serious failure of a lifting engine on a V / STOL plug tool, the plug tool driven at the rear tends to roll, this concept of deflection up and down can be a considerable advantage.

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The invention is explained below with reference to one in
Drawing illustrated Ausftihrungsbeispiels explained in more detail.
In the drawing:

Flg. 1 a jet engine in a side seat

opinion,. ι

Fig. 2 is a half section through the engine cowling, j

3 shows a half section through the deflecting elements;

the pivot centerlines, '

4, 5 and 6 three side views with different
Positions of the deflection elements and

7 shows half a longitudinal section in the area of the deflecting elements. ;

In Fig. 1, 2, 3 and 7, a jet engine 12 is with

high by-pass ratio in an enclosure or cladding,

13 arranged. At the rear of the fairing contains the!

upper and lower wall, two deflection elements 19, which one ge j

have arched cross-section and in longitudinal section a rear,

Extension of the inner and outer cladding profile dar- i

place. The deflection elements have coaxial pivot bearings 31 and j

32 on transverse journals 33, which are rigidly attached to the |

rear lateral extensions or tongues 14 of the shoot;

factory cladding are attached . Inside the interior and exterior _;

wall 21 and 22 of the cladding are at 17 two actuation '

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devices 16 rotatably mounted, and via a rotatable connection 18 are the actuators each with the associated deflection element 19 connected.

FIGS. 4, 5 and 6 show three typical deflection positions.

In Pig. 4 it can be seen that when both actuating devices 16 are actuated at the same time, the deflecting elements Pivot 19 into a position »in which it is symmetrical to the longitudinal center line lie and close the rear exit of the jet pipe, their internal shape being such that they are symmetrical Redirection of the engine exhaust in the direction of the file j and these exhaust gases exit through upper and lower openings 40 released as a result of the pivoting.

i FIGS. 5 and 6 show that with constant differential adjustment of the actuating devices, the deflecting elements are common can be pivoted either clockwise or counterclockwise about the pivot point 15, so that the direction of the deflected Thrust between the two final states shown! Is changeable, in which the entire engine exhaust gases either upwards (fig. 5) or downwards (fig. 6).

- patent claims -

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Claims (8)

Claims ΤΟΙι or V / STOL plug stuff with thrust deflector at the outlet of the jet pipe or the engine cowling, characterized in that at least two independently rotatable deflection elements (19) are provided in the direction of forward thrust, duroh which deflects the normal gas flow in a vertical or almost vertical direction and is then released through one or more openings (40) in the jet pipe or j in the engine cowling (13), which are automatically released when the elements are rotated. 2. Plugzeug according to claim 1, characterized in that the deflecting elements (19) in their non-rotated position form upper and lower end parts of the engine cowling and that each part is double-walled and the profiles of the walls on the outside by aerodynamic aspects and on the inside by the requirements of the flow the engine exhaust gases are determined. 3. plug stuff according to claim 1, characterized in that the um- . steering elements (19) arched and with normal travel! ^! flight stowed in the profiles of the engine cowling 209832 / 00S3 are that they have the openings (40) for the vertical thrust bridge as smooth surfaces. 4. plug stuff according to claim 2 or 3, characterized in that. that ι the deflection elements (19) are rotatably arranged on transverse bearings mounted on the engine cowling and that the bearings have a common horizontal axis of rotation which runs through the longitudinal axis of the engine. 5. Aircraft according to claim 2 and 4 » characterized in that the bearings for the deflection elements (19) sit on rear extensions or tongues (14) on the stationary engine housing or the engine cowling. 6. Plug tool according to one of the preceding claims, characterized in that separate actuating devices (16) for each deflecting element (19) are provided in such a way that either common or differential actuation of the two deflecting elements is possible. 7. Plugzeug according to claim 6, characterized in that the actuating devices (16) optionally in such a way to act : can be brought that a) both deflection elements (19) can be pivoted in the direction of the center line of the engines until they meet and open an upper and a lower outlet for the engine exhaust gases; b) only the lower deflecting element waits until it hits the upper deflecting element and is thereby pivotable 209832/0053 2202A1 5 a lower exit opening is created or i o) in the upper deflecting element take down to the on to the lower deflecting element is pivotable and thereby an upper outlet opening is provided. 8. Plugzeug according to claim 7, characterized in that at least two forward engines are arranged at the rear on opposite sides of the fuselage , which are each equipped with two deflecting elements in order to be able to generate a rolling moment by differen iel-Ie actuation. 209832 / 00S3 Blank page