SE0801636A0 - Rotor wing for VTOL aircraft - Google Patents

Description

15 20 25 30 35 2 will end up upside down with this solution. We are thus referred to symmetrical problems with the disadvantages this entails.

DESCRIPTION OF THE INVENTION The object of the invention is to offer a better compromise of the VTOL plan than has previously been possible, with a focus on scope and usability. This object is achieved by the plane being provided with two counter-rotating two-bladed rotors on a common geometric axis where each of these two rotors can change the angle between the longitudinal axes of the blades from about 180 degrees in hovering position to about 30..40 degrees in flying position. Furthermore, each rotor blade has a rudder that can be controlled in different ways depending on the hovering position or eye position. The hovering mode consists of two counter-rotating rotor blades where the rudders replace the normal pitch function of a helicopter. When switching to the eye position, first stop one rotor half at an angle of approx. 90 degrees to the eye direction, then wait for the other rotor half to reach an angle of 120..130 degrees towards the eye direction before stopping it. This occurs simultaneously for both rotors and results in two stationary wing pairs that have the correct orientation in relation to the direction of travel. Other advantages of the invention appear from the following description of exemplary embodiments.

LIST OF FIGURES The description of exemplary embodiments is made with reference to figures. in which: Figure 1, shows the inventive VTOL plan in the eye position.

Figure 2, shows the VTOL plan according to the plan in hovering position.

DESCRIPTION OF EMBODIMENT EXAMPLE 10 15 20 25 30 35 3 An eye plane depicted in hovering mode in Figure 2 and eye eye in Figure 1 have, in addition to the inventive rotor wing, a body (6) and normally height rudders (10) and side rudders (9). Arranged on the g plane plane body (6) are two driving propeller assemblies (7,8) which are preferably electrically driven.

In hover mode, the first rotor (1,2) rotates clockwise while the second rotor (3,4) rotates counterclockwise. In this example, all rotor halves (1,2,3,4) each have their own drive motor and each rudder, which in this mode acts as the pitch control on a helicopter. However, there are major differences from a conventional helicopter rotor, e.g. the span is greater, the speed lower and the wing profile more similar to a fl plane plane wing than a helicopter rotor. The propeller units (7,8) are used in this mode mainly for orientation of the entire fl plane and work in different directions, one drives forward as the other drives backwards and vice versa, which replaces the tail rotor in the analogy with the helicopter A consequence of the low speed is that the sound level when hovering will be relatively low. Transition to fl ygmode can e.g. take place according to the following sequence: 1. Maximum forward speed is assumed by combining pitch and cooperating propeller units (7.8). 2. The rotor halves (1) and (3) are stopped with maximum deceleration to their respective positions according to figure 1. 3. The rotor halves (2) and (4) continue their rotation until they reach their respective positions according to fi gur 1. 4. The propeller units (7 , 8) is given full effect until the cruising speed in fl yg mode is reached.

In the gr ygr node, the rudder (12) of the rotor halves switches to skew rudder function. The tail section fulfills normal function with raised rudders (l0) and side rudders (9).

This gives two wing pairs with the right profile for good performance in fl ygmode. The angle of the wing halves relative to the eye body can be easily changed to optimize eye properties in different situations because each wing half has its own drive.

Details regarding arrangements with drive and storage of wing halves in the rotomav (5) and mechanics for steering the rudder on said wing halves are not part of this application, but can be varied freely without departing from the inventive rotor wing.

To return to hovering mode, e.g. following sequence: 1. The flight speed is reduced to a minimum. 2. Front wing halves (1) and (3) are started in their respective directions of rotation until the rotor halves are parallel to the corresponding rear wing halves (2) and (4). 3. Rear wing halves (2) and (4) start in their respective directions of rotation.

F * The propeller units (7,8) return to control of orientation.

The result is a VTOL aircraft that has flying performance close to a conventional aircraft - but with capacity for vertical take-off and landing as well as hovering. Depending on which feature is prioritized, the wing profile can be adapted for optimal hovering or optimal flight or some compromise between them. If the profile e.g. optimized on the basis of hovering mode, the profile closest to the hub must be adapted for low air speed, while the profile closest to the wingtip must be adapted for significantly higher air speed. In fl ygmoden, the whole wing has basically the same air speed - and thus will not work as efficiently. To some extent, the rudder arrangement can help alleviate the negative effects of profile-related compromises. Solutions with more than one rudder per wing half are also possible.

Figure 3 shows an embodiment, in fl yg mode, which does not require separate drive of all four wing halves. The drive of the rotors is reduced to the two rotor halves (1) and (3) which in hovering mode are driven in different directions of rotation. The other rotor halves (2) and (4) are hinged relative to the rotor halves (1) and (3) in such a way that the maximum angle between rotor halves (1) and (2) and (3) and (4), respectively, is 180 degrees. . When switching to g eye mode, when the rotor halves (1) and (3) assume their stationary positions approximately 90 degrees to the fl eye direction according to figure 3 - the rotor halves (2) and (4) will simply assume a neutral position straight back of the air resistance. This embodiment has the only advantage that the rotomav (5) and the drive of the rotors become somewhat simpler.

The invention is not limited by the above described but can be varied within the scope of the appended claims. Thus, it is understood that described methods for propulsion in eye mode and control of orientation in hover mode can be varied without departing from the rotor wing according to the invention.

Nor is it necessary for rudders for maneuvering in fl ygmode to be made with height and side rudders according to the conventional tail section, as stated in the examples above.

Nor does the arrangement of the rotor halves necessarily row to the number one per wing half. A minimal configuration can be limited to two rudders on a complete rotor blade with four rotor halves, while a maximum configuration may have several rudders per wing half ~ which would provide greater opportunities to adapt the rotor blade profile to different operating cases.

Claims (4)

10 15 CLAIMS A plane plane body (6) is provided with two rotor blades (1,2) and (3,4) starting from a rotor hub (5) characterized in that the rotor halves (1,2,3,4) can partly occupy stationary positions for rocking so that the rotor wing (1,2) constitutes the left wing pair of the plane while the rotor wing (3,4) constitutes the right wing pair of the plane, and can rotate for vertical take-off and landing by placing the rotor halves (1,2) parallel to each other and rotating clockwise and the rotor halves ( 3.4) is placed parallel to each other and rotates counterclockwise. 2. Rotor blades according to claim 1, characterized in that each rotor half (1,2,3,4) has its own drive motor. 3. Rotor blades according to claim 1, characterized in that at least two of the rotor halves (1,2,3,4) have at least one steerable rudder (12). Aircraft with rotor wings according to claim 1, characterized in that the fuselage body is provided with a propeller unit (7) on the left side and a propeller unit (8) on the right side which can co-operate for propelling the plane, and can propel in different directions for orientation. and control when hovering.