Remote electro-aeroplane

[0002] The invention relates to a model aeroplane and, in particular, to a remote electro-aeroplane.

[0003] Conventionally, the empennage of a model aeroplane typically consists of a stabilizer and a control rudder surface having single-piece structure and controlled by two servos. Depending on their empennages, there are two types of model aeroplane in general: elevator-rudder type and V-tail type. In the elevator-rudder type plane, the elevator and the rudder are controlled respectively by two servos arranged in a remote control unit within the body, and the elevator as well as the rudder are adjusted at the same time to prevent the plane from spiral down when it makes a turn. Thus, the operation of it is so complicated that it often brings about spiral down against normal fly due to any operation mistake, and is hard to master for primary players. In the V-tail type plane, its left and right control surfaces are also controlled by two servos through two control rods respectively, and only enabled to move up or down at the same time when the steering rod is operated in case of the plane turning a corner. As a result, the plane often spirals down. To prevent substantially from spiral down during the plane making a turn, the solution in prior art is a simultaneous operation of the elevating rod for compensating the loss of lift due to turning however, it makes the aeroplane complicated in structure with troublesome operations.

[0004] An object of the invention is to provide a remote electro-aeroplane, particularly intended for primary players, having a simple structure with easy control and capable of maintaining steady fly in case of turning a corner.

[0005] To achieve said object, the invention provides a remote electro-aeroplane comprising a body, a wing, a power means, a remote receiving means and a V-type empennage comprised of a left tail stabilizer, a left turn rudder surface, a right tail stabilizer and a right turn rudder surface made of elastic foaming material and having a layer of plastic film attached on their upper and lower surfaces, characterized in that the left turn rudder is jointed to the left tail stabilizer by the plastic film attached on their upper surfaces with a separation of the elastic foam from the plastic film on lower surface at their joint, forming a cross-section of the left tail stabilizer and a cross-section of the left turn rudder surface at the joint respectively, and the right turn rudder surface is jointed to the right tail stabilizer in same manner, forming a cross-section of the right tail stabilizer and a cross-section of the right turn rudder surface at their joint respectively, wherein a left rack and a right rack are arranged on the left and the right turn rudder surfaces respectively, a left flexible cable is connected to the upper section of rudder surface for the left rack with its one end and to a servo means within the remote receiving means with its another end, a right flexible cable is connected to the upper section of rudder surface for the right rack with its one end and to a servo means within the remote receiving means with its another end, and the restoration mechanisms are provided beneath the left and the right turn rudder surfaces respectively.

[0006] The restoration mechanism is a rubber band with its one end fixed on the lower surface of the tail stabilizer and its another end fixed on the lower surface of the corresponding turn rudder surface.

[0007] Alternately, the restoration mechanism is a single rubber band with its one end connected to the lower section of rudder surface for the left rack and its another end connected to the lower section of rudder surface for the right rack via the front of the tail rack fixed between the tail pole and the joint of left and right empennages.

[0008] Furthermore, the servo means comprises a servo or two electromagnets, and the flexible cable can replaced by a nylon wire.

[0009] Comparing to the counterpart in prior art, the aeroplane according to the invention needs only one control rod to operate, and has the advantages of a simple structure with easy control to prevent from spiral down during the aeroplane turning a corner.

[0010] FIG. 1 is a schematic drawing of the structure in a preferred embodiment of the invention.

[0011] FIG. 2 is a side view of the structure in FIG. 1.

[0012] FIG. 3 is a rear view of the structure in FIG. 1.

[0013] FIG. 4 is an enlarged perspective view of right empennage during left turn for the embodiment shown in FIG. 1.

[0014] FIG. 5 is an enlarged perspective view of left empennage during right turn for the embodiment shown in FIG. 1.

[0015] FIG. 6 is a schematic drawing of the structure in another preferred embodiment of the invention.

[0016] FIG. 7 is a side view of the structure in FIG. 6.

[0017] FIG. 8 is a rear view of the structure in FIG. 6.

[0018] FIG. 9 is an enlarged perspective view of the empennage during left turn for the embodiment shown in FIG. 6.

[0019] FIG. 10 is an enlarged perspective view of the empennage during right turn for the embodiment shown in FIG. 6.

[0020] Referring to FIG. 1 through FIG. 5, a preferred embodiment of the invention is shown. The aeroplane according to the preferred: embodiment of the invention comprises a body 50, a wing 60, a power device 70, a remote receiving device 40 and a V-type empennage composed of a left tail stabilizer 10, a left turn rudder surface 11, a right tail stabilizer 20 and a right turn rudder surface 21. Generally, the empennage is made of elastic foaming material with a layer of plastic film attached on the upper and lower surfaces. The invention is improved in that the left turn rudder surface 11 is jointed to the left tail stabilizer 10 by the plastic film attached on their upper surface with a separation of the elastic foam from the plastic film on their lower surface at their joint, forming a cross-section 15 of the left tail stabilizer 10 and a cross-section 16 of the left turn rudder surface at the joint respectively due to the thickness of elastic foam. The right tail stabilizer 20 is jointed to the right turn rudder surface 21 in the same manner, and cross-section 25 of the right tail stabilizer 20 and a cross-section 26 of right turn rudder surface are formed at the joint respectively. On the upper faces of the left and the right turn rudder surfaces 11 and 21, there are a left and a right racks 14, 24 respectively. A left flexible cable 13 is connected to the left rack 14 with its one end and to a servo 41 in the remote receiving device 40 with its another end. Similarly, a right flexible cable 23 is connected to the right rack 24 and the servo. Two restoration mechanisms 12 and 22 are provided beneath the left and the right turn rudder surfaces 11 and 21 respectively. They may adopt rubber bands with better elasticity, two ends of which are fixed on the lower face of the tail stabilizer and the lower face of the corresponding turn rudder surface respectively.

[0021] When the remote electro-aeroplane according to the invention is flying straightforwardly, as shown in FIG. 1, the left tail stabilizer 10 and the left turn rudder surface 11 are in a same horizontal plane, and their cross-section 15 and cross-section 16 are met and coincided with each other; also, the right tail stabilizer 20 and the right turn surface 21 are in a same horizontal plane, and their cross-sections 2526 are met and coincided with each other.

[0022] When the aeroplane is turning left, as shown in FIG. 1 and FIG. 4 , under the control from the remote receiving device 40, the servo 41 turns in anti-clockwise direction to drive the right flexible cable 23 connected on it, thereby the right turn rudder surface 21 is pulled up by the right flexible cable 23 through the right rack 24. Meanwhile, although the servo 41 turns left to drive the left flexible cable 13, the left turn rudder surface can not be pushed down through the left rack, since the cable 13 is flexible, and maintains its original position because of the cross-section 15 and the cross-section 16 leaned against each other. When the aeroplane changes its turning fly to straightforward fly, the right flexible cable 23 will be restored by the control to the servo 41 in the remote receiving device 40, while the right turn rudder surface 21 will be restored by a back pull spring from the restoration mechanism 22, and will not be pulled to the downward position by such spring because its cross-section 26 will rest against the cross-section 25 of the right tail stabilizer 20.

[0023] When the aeroplane is turning right, as shown in FIG. 1 and FIG. 5, the rudder turns in clockwise by the control from the remote receiving device 40, the desired right turn can be achieved by the operations opposite to those in the left turn process described above.

[0024] Another embodiment of the invention as shown in FIG. 6˜FIG. 10 is characterized in that the restoration mechanism is a single rubber band with its one end connected to the lower section of rudder surface for the left rack 14 and another end connected to the lower section of rudder surface for the right rack 24 through the front of the tail rack 18 fixed between the tail pole 17 and the joint of left and right empennages. Thus, the rubber band is divided into a left part 12 and a right part 22. The fly operations of this embodiment are similar to those in the above embodiment.

[0025] In both embodiments described above, the servos can be replaced by two electromagnets, and the flexible cable can be replaced by a nylon wire. Moreover, the operation principle of the invention will be described in below. Namely, there are two resolution forces from the air force acting on the turn rudder surface when the aeroplane turns: a horizontal force perpendicular to the body to turn the aeroplane; and a downward force perpendicular to the body. It is the later that provides a lift up to the head of aeroplane to ensure a smooth turning of the aeroplane without spiral down.