GB2318989A

GB2318989A - Model aircraft

Info

Publication number: GB2318989A
Application number: GB9722230A
Authority: GB
Inventors: Martin Smida
Original assignee: WUPPER EXQUISIT VERTRIEB EWALD
Current assignee: WUPPER EXQUISIT VERTRIEB EWALD
Priority date: 1996-10-26
Filing date: 1997-10-21
Publication date: 1998-05-13
Also published as: GB9722230D0; FR2755033A1; CN1180580A; DE29618665U1

Abstract

A model aircraft includes a base body 11 to which is attached at least one blade wheel 12 so as to be rotatable about an axis of rotation, and at least one helical spring 14 supporting the base body and the at least one blade wheel. The model aircraft further includes means 15 for an easily or freely rotatable bearing of the at least one blade wheel, wherein the at least one blade wheel includes a device 16 for changing the direction of rotation. Means 15 suitably takes the form of rivets (20, 21, Figure 2), positioned in a through opening (17) of the blade wheel 12. Device 16 takes the form of inclined blades attached to the blade wheel.

Description

MODEL AIRCRAFT 1 2318989 BACKGRO OF THE INVENTI

1. Field of the Invention

The present invention relates to a model aircraft including a base body to which is attached at least one blade wheel so as to be rotatable about an axis of rotation, and at least one helical spring supporting the base body and the at least one blade wheel.

2. Descriiption of the Related Art Various embodiments of model aircraft of the above-described type are known in the art. For example, model aircraft are known with a blade wheel which is mounted so as to be rotatable about an axis of rotation, wherein the blade wheel is composed, for example, of several wood blades which are joined together in the middle portion thereof, for example, by gluing. These embodiments have the disadvantage, on the one hand, that these blade wheels are difficult to rotate, i.e., at least are not easily rotatable; on the other hand, the blade wheels always rotate in the same direction during the upward movement as well as during the downward movement of the model aircraft.

2 Also known in the art are embodiments with an improved bearing of the blade wheel; in that case, the bearing of the blade wheel is effected by means of a wire pin which tapers toward a tip, for example, a needle. In that case, a greater stability of the bearing of the blade wheel would be desirable; in addition, it is disadvantageous also in this case that the blade wheels always rotate in the same direction during the upward and downward movements of the model aircraft.

3 SUMDWY OF THE INVENTI Therefore, it is the primary object of the present invention to provide a model aircraft of the above-described type in which the deficiencies mentioned above are eliminated. Specifically, the bearing of the blade wheel is to be improved and the blade wheel should rotate in different directions of rotation during the upward movement and the downward movement of the model aircraft.

In accordance with the present invention, the model aircraft includes means for an easily or freely rotatable bearing of the at least one blade wheel, wherein the at least one blade wheel includes means for changing the direction of rotation.

As a result of the configuration according to the present invention, it is achieved for the first time in a simple manner that the bearing of the blade wheel of a model aircraft is constructed in a freely rotatable and stable manner, and that, in addition, it is made possible that the blade wheels rotate in respectively different directions of rotation during the upward and downward movements of the model aircraft.

4 In accordance with a preferred embodiment of the present invention, the means for changing the direction of rotation of the at least one blade wheel are constructed in such a way that the at least one blade wheel has a plurality of blades which are arranged in an inclined position relative to the direction of rotation of the blade wheel. This makes it possible, due to the respective uplift at the blades during the upward and downward movements, that the blade wheel is rotated in the respective direction of rotation. The blades of the at least one blade wheel are preferably inclined approximately at an angle of 45 degrees relative to the direction of rotation.

In the preferred embodiment of the present invention, the blade wheel has four blades.

In accordance with another useful feature, the means for the freely rotatable bearing of the at least one blade wheel are constructed in such a way that the blade wheel is supported by two rivets on the axis of rotation of the base body, wherein the rivets extend over the inner side of a throughopening of the blade wheel for the axis of rotation. This configuration facilitates a free or easy rotation of the blade wheel on the axis of rotation in the respective direction of rotation. It is recommended that the rivets are constructed so as to engage around the respective ends of the throughopening so as to form an upper and lower stop for the at least one blade wheel. This further improves the free rotatability of the blade wheel in the respective direction of rotation.

In accordance with a further development of the present invention, the axis of rotation is formed by a bolt secured to a support element for the blade wheel arranged on the upper side of the base body. As a result, the construction of the axis of rotation is realized in a simple manner. It is recommended in this regard that the support element for the blade wheel has a rivet on its upper portion on the side facing the blade wheel, wherein the rivet engages around the upper side of the upper portion of the support element for the blade wheel so as to form a stop. This feature also improves the free rotatability of the blade wheel in the respective direction of rotation.

In addition, it is recommended that a cover cap is provided on the bolt on the side of the blade wheel facing away from the base body. This cover cap preferably has at the upper side a hook screwed into the cover cap, wherein the spring is fastened to the hook.

6 The various features of novelty which characterize the invention are pointed out with particularity in the claims annexed to and forming a part of the disclosure. For a better understanding of the invention, its operating advantages, specific objects attained by its use, reference should be had to the drawing and descriptive matter in which there are illustrated and described preferred embodiments of the invention.

7 BRIEF DESCRIPTION OF THE DRAWING

In the drawing:

Fig. 1 is a side view of a model aircraft in accordance with the present invention; and Fig. 2 is a partial sectional view of the bearing point of the blade wheel of the model aircraft according to the present invention.

8 DESCRIPTION OF THE PREFERRED EMBODIMENTS

The model aircraft according to the present invention is generally denoted by reference numeral 10. The aircraft model 10 is composed of a base body 11, wherein a blade wheel 12 is fastened to the base body 11 so as to be rotatable about an axis of rotation 19. The model aircraft 10 additionally has a spring 14 for supporting the base body 11 and the blade wheel 12. The model aircraft 10 further includes means 15 for a freely or easily rotatable bearing of the blade wheel 12 and the blade wheel 12 has means 16 for changing the direction of rotation.

The means 16 for changing the direction of rotation of the blade wheel 12 are constructed in such a way, as particularly shown in Fig. 1 of the drawing, that the blade wheel 12 has a plurality of blades 13 which are in an inclined position relative to the direction of rotation of the blade wheel 12. In this manner, the respective uplift at the blades 13 causes the respective direction of rotation during the upward and downward movements.

In accordance with a preferred embodiment of the present invention, the blades 13 of the blade wheel 12 are inclined approximately at an angle of 45 degrees relative to the direction 9 of rotation. In the embodiment shown in Fig. 1 of the drawing, the blade wheel 12 has four blades 13. However, it is possible to vary the number of blades.

The means 15 for the freely rotatable bearing of the blade wheel 12 are constructed in such a way, as particularly shown in Fig. 2 of the drawing, that the blade wheel 12 is supported on the axis of rotation 19 of the base body 11 by means of two rivets 20 and 21 extending over the inner side 18 of its throughopening 17 for the axis of rotation 19. This ensures that the blade wheel 12 can easily slide on the axis of rotation 19 in the respective direction of rotation. The rivets 20 and 21 are constructed so as to engage around the respective ends 22 and 23 of the throughopening 17 so as to form an upper and lower stop 24 and 25, respectively. This further improves the free rotatability of the blade wheel 12.

The axis of rotation 19 is formed by a bolt 27 which is secured in a support element 26 for the blade wheel 12 mounted on the upper side of the base body 11. During the rotation of the blade wheel, the rivets 20 and 21 slide in the respective direction of rotation on the stop locations 39 and 40 on the bolt 27.

The support element 26 for the blade wheel 12 has a rivet 29 on the upper side 28 of the support element 26 on the side facing the blade wheel 12. The rivet 29 engages around the upper side of the upper portion 28 of the support element 26 and forms a stop 32 as a result. This further improves the free rotatability of the blade wheel 12 in the respective direction of rotation. During the rotation of the blade wheel 12, the rivet 29 slides in the respective direction of rotation on the stop location 41 on the bolt 27.

A cover cap 30 is provided on the bolt 27 on the side of the blade wheel 12 facing away from the base body 11. The cover cap 30 has on the upper side thereof a hook 31 screwed into the cap 30 for attaching the helical spring.

The base body 11 of the model aircraft 10 further includes a figure 33 with a head 34 and neck 35, and with a body 36 and legs 39 and arms 38 attached to the body 36.

When the model aircraft 10 is put into a swinging motion through the. spring 14, the blade wheel 12 will move during the downward movement in an opposite direction of rotation as compared to the upward movement; for example, during the downward movement, the blade wheel 12 rotates in a counter- 11 clockwise direction and during the upward movement, the blade wheel rotates in a clockwise direction. The bearing of the blade wheel 12 is freely rotatable and stable.

The embodiments of the invention illustrated in the drawing are examples only and the invention is not limited to these embodiments. Rather, various modifications and constructions are possible. For example, the model aircraft may be configured differently as shown in the drawing. The same is true for the configuration of the bearing of the blade wheel and the blade wheel itself. Especially the blades can be varied and the number of blades is also variable. It is also conceivable to arrange the blade wheel differently on the base body and the manner of connecting the helical spring can be changed.

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Claims

I claim:

1. A model aircraft comprising a base body and at least one blade wheel mounted on the base body so as to be rotatable in a direction of rotation about an axis of rotation, and at least one spring for supporting the base body and the at least one blade wheel, further comprising means for a freely rotatable bearing of the at least one blade wheel, wherein the at least one wheel comprises means for changing the direction of rotation.

2. The model aircraft according to claim 1, wherein the means for changing the direction of rotation of the at least one blade wheel comprises a plurality of blades attached to the at least one blade wheel in an inclined position relative to the direction of rotation of the at least one blade wheel.

3. The model aircraft according to claim 2, wherein the blades of the at least one blade wheel are approximately inclined at an angle of 45 degrees in relation to the direction of rotation.

4. The model aircraft according to claim 2, wherein the at least one blade wheel has four blades.

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5. The model aircraft according to claim 1, wherein the at least one blade wheel comprises a throughopening for the axis of rotation, the throughopening having an inner side, the means for the freely rotatable bearing of the at least one blade wheel comprising two rivets mounted on the axis of rotation of the base body and extending over the inner side of the throughopening.

6. The model aircraft according to claim 5, wherein the rivets have ends engaging around ends of the throughopening, wherein the ends of the rivets form an upper stop and a lower stop, respectively, for the blade wheel.

7. The model aircraft according to claim 5, comprising a support element for the blade wheel mounted on an upper side of the base body, the axis of rotation comprising a bolt secured to the support element.

8. The model aircraft according to claim 7, wherein the support element for the blade wheel has at an upper portion thereof facing the blade wheel a rivet, wherein the rivet engages over the upper portion of the support element for the blade wheel so as to form a stop.

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9. The model aircraft according to claim 7, further comprising a cover cap mounted on the bolt on a side of the blade wheel facing away from the base body.

10. The model aircraft according to claim 9, further comprising a hook screwed into an upper side of the cover cap for attaching the spring.

11. A model aircraft comprising a body suspended on a spring and having at least one propellor mounted thereon which is freely rotatable in opposite directions during upward or downward movement of the body on said spring.

12. A model aircraft substantially as herein described with reference to the accompanying drawings.

is