WO2014094870A1

WO2014094870A1 - Rotor bearing and autogyro

Info

Publication number: WO2014094870A1
Application number: PCT/EP2012/076624
Authority: WO
Inventors: Otto Strauss; Tim Markus STRAUSS
Original assignee: Otto Strauss; Strauss Tim Markus
Priority date: 2012-12-21
Filing date: 2012-12-21
Publication date: 2014-06-26

Abstract

An autogyro (1) comprises a support structure (2) having a rotor mast (3), a rotor head (4), which is attached to the rotor mast (3) and has a rotor mount (420) having rotor articulation means (410, 411), to which a rotor (5) is attached in an articulated manner, and a propeller device (6), which is formed in such a manner that it can generate propulsion during operation of the autogyro (1). In order to provide better protection from crashing in the event of malfunctions and emergency situations, the autogyro (1) has a parachute rescue apparatus (7), which comprises at least one parachute (70) and triggering means for triggering the at least one parachute (70).

Description

Rotor bearing and gyroplane

The present invention relates to a rotor bearing according to the preamble of claim 1 and a gyroplane according to the preamble of claim 2.

Gynecopters (often referred to as gyrocopter) have long been known in the prior art in various embodiments. A gyrocopter is a so-called rotorcraft with a mounted on a rotor mast, rotatably mounted rotor and a propeller device, which is usually located in a rear area of the gyroscope and provides for propulsion of the gyrocopter. In contrast to a helicopter in which the rotor is forced to rotate by means of a drive device, the rotation of the rotor of a gyroscope is caused by the occurring wind (so-called autorotation). Although it is also possible to drive the rotor with the help of an optional Prerotators, the structural design of a gyrocopter is much easier than the construction of a helicopter. For example, in a gyroplane, unlike a helicopter, neither a swashplate nor a complicated gearbox assembly acting on the tail rotor of the helicopter is needed.

Gyroplanes are generally considered to be comparatively safe aircraft because, even in the event of failure of the propeller device generating the propulsion, the rotor continues to rotate due to autorotation. Nevertheless, even with a gyroplane under certain circumstances, critical flight situations can occur, which can result in particular from a mechanical defect in the rotor. For example, it is conceivable that the rotor is damaged due to external influences or that a rotor blade of the rotor is released from its anchorage. Such critical flight situations can be very difficult for a pilot, possibly even not flying at all be overcome, so that it can come in the worst case, a crash of the gyrocopter.

The present invention is based on the object 5 to provide a rotor bearing for a gyroplane and thus a gyrocopter of the type mentioned, the or in comparison to the known from the prior art rotor bearings or gyroscopes in malfunction and emergency situations offers a higher fall protection.

The solution to this problem provides a rotor bearing for a gyrocopter with the features of the characterizing part of claim 1 and a gyroplane of the type mentioned above with the features of the characterizing part of claim 2. The dependent claims relate to advantageous developments of the invention.

A rotor bearing according to the invention or a gyroplane according to the invention with such a rotor bearing is characterized in that a parachute rescue device is made possible, which has at least one parachute and release means for triggering the at least one parachute, in particular within the standing, that is not rotating rotor mast. According to the invention, a rotor bearing or a gyroscope is provided, which offers greater safety in the event of malfunctions and emergency situations in comparison with the gyroplanes known from the prior art. If a malfunction occurs in which the rotor of the gyrocopter is no longer or only partially functional, the parachute of the parachute rescue device can be activated, so that the gyrocopter can safely slide to the ground on the opened parachute. Even in critical situations can be achieved by a fall security.

The rotor mast preferably extends through the rotor bearing and projects beyond this with its upper mast end.

In a particularly advantageous embodiment, it is proposed that the rotor mast at an upper end of a hollow receiving space, within which the Parachute rescue device is housed, comprising a parachute outlet opening for the at least one parachute. As a result, the parachute rescue device can be accommodated in a space-saving manner inside the already existing rotor mast. An additional to be provided and the flight weight of the gyroscope increasing receiving device for the paratroop rescue device is thus not required in an advantageous manner. If the volume available in the interior of the rotor mast for the parachute rescue device is insufficient, an additional receiving body can be placed on the end of the rotor mast which penetrates the rotor bearing and which completely or partially accommodates the parachute rescue device, thus in particular in addition to the receiving space provided by the rotor mast , picks up. This allows the application of the invention also for very large parachutes or rotor masts with a small diameter.

In a preferred embodiment, the rotor mount may include a central opening through which the rotor mast extends. As a result, a compact design is achieved, which moreover enables a safe release of the at least one parachute in an emergency situation. The risk that could catch the at least one parachute on the rotor and / or on a part of the rotor head, can be advantageously reduced by this measure.

In order to enable a variable adjustment of the position of the rotor head relative to the rotor mast and thereby to provide a correspondingly large space for the activation of the at least one parachute of the parachute rescue device, in a particularly preferred embodiment there is the possibility that the rotor head is gimbal mounted on the rotor mast. Preferably, the rotor head may comprise a first gimbal, which is articulated in the axial direction of the parachute outlet opening spaced on the rotor mast and is pivotable about a first pivot axis. At this first gimbal, a second gimbal can be hinged, which is pivotable about a second pivot axis which is oriented orthogonal to the first pivot axis. This advantageously makes it possible to pivot the rotor head about the two orthogonally oriented pivot axes in the longitudinal and in the transverse direction. In a particularly advantageous embodiment, it is proposed that the central opening of the rotor mount is shaped such that it can release the parachute exit opening independently of the angular position of the rotor mount and / or the rotor head. It is thereby achieved that the at least one parachute of the parachute rescue device can always be safely released in an emergency situation. The central opening of the rotor holder can advantageously be oblong oval, in particular elliptical.

In a further advantageous embodiment, there is the possibility that the central annular openings of the gimbals are oblong oval, in particular elliptical shaped. As a result, it is likewise possible to ensure a reliable triggering of the at least one parachute of the parachute rescue device while at the same time providing a large clearance for the swiveling of the rotor head.

The parachute rescue device can be activated in particular manually by a corresponding operating intervention on the part of the pilot when a danger situation occurs. Alternatively or additionally, it may be provided that the gyroplane comprises means for automatically activating the triggering means. In an emergency situation, the parachute rescue device - for example, by a central control device of the gyrocopter - be activated.

In order to enable a reliable activation of the parachute rescue device and thus a reliable and safe release of the at least one parachute, the release means can be advantageously designed as pyrotechnic release means. Can be used in particular outside on or inside the rotor mast and / or in the rotor mast expanding receiving body mounted missile sets that tear the parachute from its recording. It can also be provided in the rotor mast or in the rotor mast expanding receiving body provided explosives or gas pressure cartridges that catapult the parachute out of his recording and in particular upwards away from the aircraft. Further features and advantages of the present invention will become apparent from the following description of a preferred embodiment with reference to the accompanying drawings. Show in it

Figure 1 is a side view of a gyroscope according to a preferred embodiment of the present invention, with activated parachute recovery device.

FIG. 2 shows a side view of a rotor mast of the gyroscope with a gimbal-mounted rotor head; FIG.

3 is a perspective view of the rotor mast with the rotor head;

Fig. 4 is a plan view of the rotor mast with the rotor head, wherein a part of the main body of the rotor head has been omitted;

Fig. 5 shows another way of housing the parachute rescue device on the rotor mast.

With reference to FIG. 1, a gyroplane 1 constructed in accordance with a preferred embodiment of the present invention comprises a support structure 2 having a closed cabin 20, a landing gear 21 on an underside of the support structure 2, and a rotor mast 3 on which a rotor head 4 with a rotor 5 is mounted. In an alternative embodiment, it is also possible to carry out the carrier structure 2 without the cab 20 or with an open cab 20. The chassis 21 is usually rigid, although an on-demand and extendable trained chassis 21 in principle is also possible.

The rotor mast 3 extending upwards away from the cabin 20 is cylindrically shaped and hollow at least in the area of an upper, free end. In the vicinity of the upper end of the rotor head 4 is arranged, the structure of which will be described below in more detail. At the rotor head 4, the rotor 5, in this embodiment two rotor blades 50, 51, attached. In principle, it is also possible for the gyrocopter 1 to have a rotor 5 with more than two rotor blades 50, 51.

On the rear side, at a rear end of the cabin 20, a propeller device 6 is mounted, by means of which the gyrocopter 1 can be driven. The propeller device 6 is preferably driven by a piston engine. Furthermore, the gyrocopter 1 has a tail 8 with a rudder 9, which - viewed in the longitudinal direction - is arranged behind the propeller device 6. In addition, the gyroplane 1 has two lateral wings 10 which are attached on both sides to the left and right of the support structure 2. It is also possible in principle to design the gyrocopter 1 without the two wings 10.

Unlike a conventional helicopter helicopter in the helicopter 1, the drive of the rotor 5 is not necessarily by means of a dedicated drive device. Rather, the propeller device 6 generates propulsion during operation of the gyrocopter 1. The rotor 5 of the gyrocopter 1 is then set in rotation due to the wind. This behavior of the rotor 5 is also called autorotation. The rotor 5 rotating on the basis of the autorotation generates a lift when the rotor surface is inclined backwards. Due to the autorotation of the rotor 5, a failure of the propeller device 6 in the vast majority of cases is not critical because the rotor 5 can continue to rotate due to the air flow. A defect or complete failure of the rotor 5, however, leads to critical flight conditions that are very difficult, possibly even impossible to control by a pilot, so that it can possibly lead to a crash of the gyrocopter 1.

To remedy this problem, the gyrocopter 1 has a parachute rescue device 7 with a parachute 70 which can be activated in an emergency situation. The parachute recovery device 7 is housed in the non-use state in a receiving space 31 in the upper hollow end of the rotor mast 3. The parachute rescue device 7 comprises as a triggering means pyrotechnic means which are designed so that they can be ignited in the event of an emergency situation and trigger the parachute 70 so that it can emerge from the parachute outlet opening 30 at the upper end of the rotor mast 3 and - as shown in Fig. 1 - can span. With activated parachute 70, the gyroplane 1 can then safely slide to the ground.

The activation of the parachute rescue device 7 can be carried out by the pilot via a suitable, in particular manually operable activation means (for example via an activation lever or activation switch). Alternatively or additionally, it is also possible that the parachute rescue device 7 is connected to a central control device of the gyrocopter 1, which is designed so that it can automatically trigger the pyrotechnic means of the parachute rescue device 7 to activate the parachute 70 in an emergency situation. Optionally, additional pyrotechnic means may be provided, by means of which the rotor blades 50, 51 can be blown away from the rotor head 4 in an emergency situation, before the parachute rescue device 7 is in turn activated.

With reference to FIGS. 2 to 4, the structural design of the rotor head 4 will be explained in more detail below, which is designed for use with a parachute rescue device 7 accommodated in the receiving space 31 of the rotor mast 3. The rotor head 4 must be designed in such a manner that it permits unimpeded activation of the parachute 70 of the parachute rescue device 7 and in this exemplary embodiment comprises a base body 400 with two rotor impact hinge means 410, 411 on which a rotor support 420 with two rotor receptacles 421 staggered by 180 °, 422 is pivotally mounted. In each of these two rotor seats 421, 422, a rotor blade 50, 51 are attached.

The two Rotorschlaggelenkmittel 410, 411 form a pivot axis, which allows pivoting of the rotor mount 420 and thus also of the rotor 5 with its two rotor blades 50, 51 in the vertical direction. In the autorotation of the rotor 5, the rotor blade 50, 51 leading in the direction of rotation and with respect to the direction of wind flow briefly moves upwards out of the plane of rotation with respect to the plane of rotation of the rotor 5, whereas the one lagging behind in this respect Rotor blade 50, 51 briefly moved downwards out of the plane of rotation. The rotor impact hinge means 410, 411, which allow the rotor blades 50, 51 of the rotor 5 to move vertically, compensate for the forces involved. Each of the two rotor blades 50, 51 is associated with a buffer means 10, 11, which is designed to limit a pivoting movement of the rotor 5 about the pivot axis formed by the two rotor hinge means 410, 411 in the direction of the base body 400 and thereby prevent the Rotor blades 50, 51 are damaged in contact with the main body 400. The buffer means 10, 11 are for this purpose made of an elastic material, in particular of rubber, and are each mounted in a, the respective rotor blade 50, 51 facing portion of the base body 400. Viewed from above, the two buffer means 10, 11 are arranged in the circumferential direction opposite one another between the two rotor impacting means 410, 411. Typically, the rotor impact hinge means 410, 411 allow the rotor mount 420 to pivot about + 8 °. Both the main body 400 and the rotor support 420 each have a central opening 401, 423, through which the rotor mast 3 is passed during assembly before it is fixed to the rotor mast 3.

The rotor head 4 of the gyroscope 4, which comprises the main body 400 with the rotor holder 420, is gimballed to the rotor mast 3. As can be seen in particular in Fig. 4, a first gimbal 8 is provided for this purpose, which is pivotally connected to the rotor mast 3 by means of a pair of first universal joint means 80, 81 which are arranged offset by 180 ° to each other. The first gimbal 8 has an elongate oval shaped (preferably elliptical) ring opening 82 which has a smaller diameter in a connecting line between the two universal joint means 80, 81 than orthogonal thereto. A second gimbal 9, which also has an elongate oval shaped (preferably elliptical) ring opening 92, is pivotally connected to the first gimbal 8 by means of a pair of second gimbal means 90, 91, which are arranged offset by 180 ° to each other. The oblong oval-shaped annular opening 92 of the second gimbal 90 also has a smaller diameter in a connecting line between the second universal joint means 90, 91 than orthogonal thereto. The first Universal joint means 80, 81 thus form a first pivot axis which is oriented orthogonal to a second pivot axis formed by the second universal joint means 90, 91. By means of the first and the second pivot axis, the rotor head 4 can be pivoted in the longitudinal direction and in the transverse direction by the pilot of the gyrocopter 1 via steering linkage 12 coupled to the rotor head, corresponding to the flight situation.

The central opening 423 of the rotor mount 420 is shaped such that it can not extend beyond the parachute outlet opening 30 at the upper end of the rotor mast 3 both at maximum angular deflection of the rotor mount 420 and at maximum angular deflection of the rotor head 4. This ensures that the parachute 70 of the parachute recovery device 7 can open and clamp unhindered after activation. In the present case, the central opening 423 of the rotor mount 420 is elongated oval (preferably substantially elliptical) and narrower between the two Rotorschlaggelenkmitteln 410, 411 than between the offset by 180 ° rotor seats 421, 422. For rotatably supporting the base body 400 with the attached thereto Rotor support 420 is provided in this embodiment on the base body 400, a ring bearing means 430, which is designed so that the base body 400 can rotate relative to the gimbaled suspended part of the rotor head 4. Other structural configurations, which can result in a rotation of the rotor 5 as a result, are also possible.

As can be seen in Fig. 4, the gyroplane 1 in this embodiment, in addition to a motor-driven, rotatably mounted Prerotator 13 which is formed serrated along its outer periphery. The teeth 130 of the prerotator 13 may engage and mesh with corresponding teeth 402 formed along the outer circumference of the ring bearing means 430. As a result, the rotor 5 of the gyrocopter 1 can additionally be set in rotation. Other coupling means for the mechanical coupling of the Prerotators 13 with the base 400 are also possible. By way of example, the coupling via a belt, a chain or the like should be mentioned in this context. Such a motor-driven prerotator 13 does not necessarily have to be present in the gyroplane 1, but is optional. FIG. 5 shows an alternative or supplementary embodiment to the embodiment shown in FIG. 1. If the volume available in the interior of the rotor mast for the parachute rescue device is not sufficient to completely accommodate the parachute rescue device, for example because a rather small rotor mast diameter is preferred from the design point of view, an additional receiving body 33 can be placed on the end of the rotor mast penetrating the rotor bearing which accommodates the parachute rescue device completely or in part, that is to say in particular in addition to the receiving space provided by the rotor mast. The receiving body is preferably releasably attached to the non-rotating rotor mast. The interior of the rotor mast and the interior of the receiving body 33 are preferably connected to one another by an opening (not shown) provided at the bottom of the receiving body 33, so that the parachute rescue device can be located both in the rotor mast and in the receiving body 33. It can also be provided that the release means are housed in the rotor mast and the parachute in the receiving body 33. In this case, it would be possible to form the receiving body 33 as a disposable receiving body, which can be blasted off of the provided in and / or on the rotor mast, if necessary, and would then be lost. Only the parachute lines would have to be securely connected to the rotor mast via suitable resilient means. The receiving body itself could be designed as a simple, low-load component, for example, of a plastic body, which would be easy and could be attached with little effort to the rotor mast. This would facilitate the maintenance of both the rotor bearing and the parachute.

Claims

claims

1. Rotor bearing for supporting a rotor (5) on a stationary rotor mast (3), wherein the rotor bearing has a rotor head (4) for attachment to a rotor mast (3) and a rotor mount (420) with rotor impact coupling means (410, 411), in which the rotor (5) is articulated, characterized in that the rotor holder (420) provides a central opening through which a rotor mast (3) having a parachute rescue device (7) is able to extend.

2. gyroplane (1), comprising a support structure (2) with a rotor mast (3), a rotor head (4) which is mounted on the rotor mast (3) and a rotor mount (420) with Rotorschlaggelenkmitteln (410, 411) has in which a rotor (5) is articulated, and a propeller device (6), which is designed such that it can generate propulsion during operation of the gyrocopter (1), characterized in that the gyrocopter (1) has a parachute rescue device (7). comprising at least one parachute (70) and triggering means for triggering the at least one parachute (70).

3. gyrocopter (1) according to claim 1, characterized in that the rotor mast (3) at an upper end a hollow receiving space (31), within which the parachute recovery device (7) is housed, with a parachute outlet opening (30) for the at least one Parachute (70) includes.

4. gyrocopter (1) according to claim 1 or 2, characterized in that the rotor holder (420) comprises a central opening (423) through which the rotor mast (3) extends therethrough.

5. gyrocopter (1) according to one of claims 1 to 3, characterized in that the rotor head (4) is gimbal-mounted on the rotor mast (3).

6. gyrocopter (1) according to claim 4, characterized in that the rotor head (4) comprises a first gimbal (8) which is articulated in the axial direction of the parachute outlet opening (30) spaced on the rotor mast (3) and a first Schwen kachel is pivotable, and in that on the first gimbal (8), a second gimbal (9) is articulated, which is pivotable about a second pivot axis which is oriented orthogonal to the first pivot axis.

7. gyrocopter (1) according to one of claims 3 to 5, characterized in that the central opening (423) of the rotor holder (420) is shaped such that it the parachute outlet opening (30) regardless of the angular position of the rotor mount (420) and / or the rotor head (4) can release.

8. gyrocopter (1) according to claim 6, characterized in that the central opening (423) of the rotor holder (420) oblong oval, in particular elliptical shaped.

9. gyro (1) according to one of claims 5 to 7, characterized in that the central annular openings (82, 92) of the gimbal rings (8, 9) oblong oval, in particular elliptical, are formed.

10. gyrocopter (1) according to one of claims 1 to 8, characterized in that the gyroplane (1) comprises means for automatically activating the release means.

11. gyrocopter (1) according to one of claims 1 to 9, characterized in that the release means are designed as pyrotechnic release means.