DE102005033697A1 - Control surface e.g. rudder, operating mechanism for airplane, has gearing placed downstream of hydraulic motor so that drive shaft of motor drives input shaft of gearing, and output shaft coincides with rotational axis of rudder - Google Patents

Abstract

The operating mechanism has a toothed gearing (2) including an input shaft and an output shaft. The gearing is placed downstream of a hydraulic drive motor (1), so that required torque output for a control surface such as rudder (12), is built up. A drive shaft of the motor drives the input shaft of the gearing, and the output shaft coincides with a rotational axis (3) of the rudder. The motor is supplied with hydraulic energy via a hydraulic tube (9). The mechanism can have more than one drive motor. The drive motor is operated both in left and right operations.

Description

TECHNICAL TERRITORY

The The present invention relates generally to mechanical equipment for maneuvering of an airplane. In particular, the invention relates to a novel trained rudder drive for an aircraft and use of a hydro or servo motor for one Aircraft steering gear.

BACKGROUND THE INVENTION

at known rudder drives for Aircraft and in particular for drives for the rudder of a vertical stabilizer The oars are usually with the help of several hydraulic cylinders driven. However, since hydraulic cylinders are natural and primary only To generate translational movements are capable of consuming Deflection mechanisms are provided to the translational movements to convert the hydraulic cylinder into a pivoting movement of the rudder to be able to. However, these deflection mechanisms bring additional weight and cause about it There are also additional ones Costs. In addition, in usually at least two or three hydraulic cylinders provided be in order for to ensure a certain reliability and redundancy. Also by this becomes superfluous weight produced, which of course in the field of aerospace engineering undesirable is. That aside anyway relatively large and heavy Hydraulic cylinder with correspondingly high weight of around 100 kg be used as to generate the required torque for Rowing operation relatively large benefits needed become. This more so than that much of the transverse momentum the hydraulic cylinder is not directly in rotational kinetic energy can be converted. Overall, therefore, known rudder drives usually relatively heavy and beat due to the required redundancy of hydraulic cylinders as well as the needed Deflection mechanisms often with additional Cost to book.

PRESENTATION THE INVENTION

It It is an object of the invention to provide a more cost effective rudder drive disposal to put, which brings less weight than a known Rudder drive corresponding performance using hydraulic cylinders.

Of the The present invention is based on the idea of a pivoting movement an aircraft helm is not about the detour of converting a translational motion into a rotational one Movement to accomplish, but rather the rotational pivotal movement to create the aircraft rudder directly. Served for this the invention of a drive motor whose rotational energy for Generation of the pivoting movement of the aircraft rudder is used.

According to one The first aspect of the present invention therefore becomes a rudder drive for a proposed about a rotation axis pivotable aircraft rudder, the a drive motor with which the pivoting movement of the aircraft rudder is brought about. By the drive motor is activated, thus at least indirectly generates a pivoting movement of the aircraft rudder about its axis of rotation become. If here of an indirect generation of a pivoting movement there is talk, it means that between the drive motor and the aircraft rudder various mechanical Kraftumwandlungs- and transmission means such as a transmission can be arranged.

There a drive motor usually both in the right and in the left mode can be operated, it is sufficient, only one drive motor to provide rudder deflections to generate in both directions (right and left). Of course you can too several drive motors for the rudder drive are used, on the one hand, if necessary to generate required torque power and on the other for a certain To ensure reliability.

According to one Another aspect of the invention is the drive motor with its drive shaft so arranged that the drive shaft with the axis of rotation of the aircraft rudder collapses to produce the pivoting movement of the aircraft rudder. hereby can in a direct way the kinetic energy of the drive motor in be converted into a pivoting movement of the aircraft rudder, without that unwanted mechanical losses, caused for example by friction.

Around To reduce weight, make the drive motor as small and light as possible to be able to the drive motor to be followed by a transmission, so the build up the required torque output for the aircraft rudder to be able to. In this case, the transmission is driven by the drive motor, so by the operation of the transmission in turn, the pivoting movement of the aircraft rudder is generated about its axis of rotation.

Around also possible in this case to generate little mechanical losses, for example by friction, is the input shaft of the transmission through the drive shaft of the Motor driven and the output shaft of the gearbox is arranged so that with the axis of rotation of the aircraft rudder to produce the Pivoting movement of the aircraft rudder coincides. In this case, for example the drive motor or its drive shaft at a different location be arranged as in the flight of the axis of rotation of the aircraft rudder, there only care should be taken that the output shaft of the transmission is aligned with the axis of rotation of the aircraft rudder.

Around the rotational movement of the drive shaft of the drive motor or of transmit the output shaft of the transmission to the aircraft rudder to be able to the rudder drive further comprises a force introduction fitting, which either on the drive shaft of the drive motor or on the output shaft of the transmission is arranged. The force introduction fitting can for example on the side of the output shaft or the drive shaft welded with these or screwed or otherwise connected non-positively. On pages the connection of the force introduction fitting with the aircraft rudder For example, the force introduction fitting can be glued, welded, soldered or with otherwise be frictionally connected to the aircraft rudder.

According to one Another aspect of the present invention is in the Drive motor to a hydraulic motor. For power supply of the hydraulic motor this can be connected to the hydraulic network of an aircraft. The pivotal movement of an aircraft rudder by a hydraulic motor to produce, proves due to the small and lightweight design appropriate hydromotors as particularly suitable. Furthermore can yourself relatively small hydromotors generate enormous torque output, which in turn contributes to weight savings. Alternatively, it is Of course also possible, For example, use an electric servomotor as the drive motor.

As already indicated, can with the rudder drive according to the invention any oar of an aircraft can be pivoted. So, for example Rudder, elevator, trim tab or ailerons are operated with the rudder drive according to the invention. However, it proves to be particularly advantageous for side roods the rudder drive according to the invention use, especially in side rows with the rudder drive according to the invention enormous weight savings compared to the known realization possible with hydraulic cylinders is.

According to one Another aspect of the present invention is a rudder with a fixed middle box and a swivel associated rudder proposed, which with the help of the previously controlled rudder drive is controlled. The rudder drive is doing so on the fixed center box, for example, via a torque support attached. On which on the rigidly mounted in this way rudder can in the manner described above, a rudder on the force introduction fitting be attached to the rudder drive.

According to one more Another aspect of the invention is proposed a hydro or Servomotor for to use a rudder drive, as previously described.

SHORT DESCRIPTION THE DRAWINGS

in the Below, the present invention will be described with reference to FIGS attached Drawings closer described. Show it:

1 shows possible places of use of the rudder drive according to the invention in an aircraft; and the

2 and 3 show a sectional view of a rudder with the rudder drive according to the invention, in which each of the front tail skin is cut away.

In The figures are the same or the same Elements marked with the same or corresponding reference numbers. The figures are not to scale, give however, qualitative proportions again.

DESCRIPTION AN EXEMPLARY EMBODIMENT THE INVENTION

1 shows a ordinary passenger plane 11 , which consists essentially of a fuselage, two wings, two horizontal stabilizers and a rudder. The rudder drive according to the invention is suitable, for example, for the landing flaps attached to the wings 15 or ailerons 16 to pivot. Furthermore, the rudder drive according to the invention is suitable for the elevators 14 on the rudder and the trimming rudder arranged on it 13 to pivot. In particular, however, the rudder drive according to the invention is suitable for the rudder arranged on the rudder 12 to pivot.

Based on 2 and the 3 will now be explained in more detail the rudder drive according to the invention become. The 2 and the 3 show the in the 1 Enlarged view with "A" in which the 3 Zoom out this section even larger. It is therefore referred to below 2 and 3 alike reference.

As can be seen in these figures, is on the fuselage 10 of the plane 11 a center box 8th attached to a rudder and protrudes from there in the usual way steeply upwards. How best in the 2 is to be recognized is at the center box 8th cut away the front outer skin, leaving it in the center of the center 8th the vertical tail can be seen. Next to the center box 8th The rudder further comprises a rudder 12 , of which only the rear outer skin 6 can be seen. The rudder 12 is at the center box 8th articulated via three rudder fittings 7 attached, which in turn consist of two V-shaped mutually arranged struts and the rear end spar 17 of the center box 8th are welded. In the area of the coincidence of the two struts of the rudder fittings 7 form these hinge openings 18 out, into which the rudder 12 can be hung with appropriate pins or other suitable means. Thus, the rudder can be 12 around the axis of rotation 3 panning around.

To be able to execute this pivoting process is in the vertical tail 8th . 12 a rudder drive 1 . 2 installed, with which the rudder 12 can be pivoted. The rudder drive comprises a drive motor 1 and a gear transmission 2 , wherein the drive motor 1 over a moment support 4 at the center box 8th or attached to the end spar. In the drive motor 1 it may be, for example, a hydraulic motor, which via hydraulic hoses 9 supplied with hydraulic energy. Although in the 2 and 3 a gear transmission is shown, which is the drive shaft of the drive motor 1 (not shown) is connected downstream, but can on such a gear transmission 2 with correspondingly strong dimensioned drive motor 1 possibly also be waived.

As in the 2 and 3 can be well recognized, is the drive motor 2 arranged so that its drive shaft with the axis of rotation 3 of the rudder 12 flees. In the event that no gear transmission 2 could be provided could be a force introduction fitting 5 directly on the drive shaft of the drive motor 1 be arranged, with which the rotational movement of the drive shaft of the drive motor 1 on the rear outer skin 6 of the rudder 12 could be transferred.

In the event that like in the 2 and 3 shown, however, the drive motor 1 a gearbox 2 is downstream, drives the drive shaft of the drive motor 1 the input shaft of the transmission 2 on, causing on the output shaft (not shown) of the transmission 2 an output is generated, which in turn via the force introduction fitting 5 on the rear outer skin 6 of the rudder 12 will be transferred.

As the drive motor 1 can be operated both in the right and in the left mode, no two different drive units need to be provided, as is the case in the case of the usual embodiment of a rudder drive using piston-cylinder units. Rather, it's enough, just a drive motor 1 provide, whereby the weight of the rudder drive and thus its cost can be reduced.

1

hydraulic motor

2

(Gear) gear

3

axis of rotation

4

torque support

5

Force introduction fitting

6

rudder (rear outer skin)

7

Rudder bearing fittings

8th

center box

9

hydraulic hose

10

hull

11

plane

12

rudder

13

trim tab

14

elevator

15

flap

16

aileron

17

end spar

18

hinge

Claims (10)

Rudder drive for about a rotation axis ( 3 ) pivotable aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) comprising a drive motor ( 1 ), by its activation at least indirectly a pivoting movement of the aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) about its axis of rotation ( 3 ) is produced. Rudder drive according to claim 1, wherein the drive motor ( 1 ) identifies a drive shaft and wherein the drive motor ( 1 ) is arranged with its drive shaft so that the drive shaft with the axis of rotation ( 3 ) of the aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) for generating the pivoting movement of the aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) coincides. Rudder drive according to claim 1 or 2, wherein the rudder drive further comprises a transmission ( 2 ), which by the drive motor ( 1 ) is driven, and by its operation, the pivoting movement of the aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) about its axis of rotation ( 3 ) is produced. Rudder drive according to claim 3, wherein the transmission ( 2 ) comprises an input shaft and an output shaft, wherein the drive shaft of the drive motor ( 1 ) the input shaft of the transmission ( 2 ) drives and the output shaft with the axis of rotation ( 3 ) of the aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) for generating the pivoting movement of the aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) coincides. Rudder drive according to claim 3 or 4, wherein the rudder drive further comprises a force introduction fitting ( 5 ), which on the output shaft of the transmission ( 2 ) is arranged, and a rotational movement of the output shaft to the aircraft rudder ( 12 . 13 . 14 . 15 . 16 ) transmits. Rudder drive according to one of the preceding claims, wherein the drive motor is a hydraulic motor ( 1 ). Rudder drive according to one of the preceding claims, wherein the drive motor ( 1 ) is a servomotor. Rudder drive according to one of the preceding claims, wherein the aircraft rudder is an aircraft rudder of the group consisting of rudders ( 12 ), Elevator ( 14 ), Trim tab ( 13 ) and ailerons ( 16 ). Vertical stabilizer with a fixed center box ( 8th ) and a swiveling rudder ( 12 ) which is controlled by a rudder drive according to any one of the preceding claims. Use of a hydraulic motor ( 1 ) or a servomotor for a rudder drive according to one of claims 1 to 8 for generating a pivoting movement of an aircraft rudder ( 12 . 13 . 14 . 15 . 16 ).