Spoiler for wings

Details Spoiler for wings Spoiler for wings

1999-11-16

2001-10-09

Jordan, Charles T. (Department: 3644)

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

Reexamination Certificate

active

06299109

ABSTRACT:

BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention relates to a spoiler for wings, in particular plane wings, which spoiler is unfoldable during the landing and take-off of the plane or the like and retractable during cruising.
Although, in the following, the use of the spoiler according to the invention is exclusively discussed in connection with the wings of airplanes, its application theoretically is conceivable also with other types of aircraft and other vehicles such as, for instance, high-speed ships or high-speed cars.
The term spoiler serves to denote a deflector provided on the rear upper side of a wing, which, on the one hand, serves as an air brake during landing and, on the other hand, also assists the aileron by asymmetrical use. The English term “spoiler” goes back to the fact that it creates a resistance, thereby annihilating part of the lift.
2. Prior Art
CH 683 982 A5 describes a device for increasing the lift on a plane wing in the form of an air-conducting element, which also may serve as a spoiler after landing.
In order to enable the progressive movement of a plane or the like in the air, a force must act on the same in a sense opposite to the force of gravity. This is obtained through the lift generated by the airfoils or wings of the plane. By appropriately configuring the sections of the wings, the air resistance to the lift is minimized. During the landing of a plane, and in order to reduce the landing run, a reduction of the lift is required. To this end, so-called spoilers or deflectors/air brakes are provided on the surfaces of the wings, which are extended during and after landing thus generating a resistance.
In order to cope with the air traffic, airplanes that become larger and larger are being built for accommodating an increasing number of passengers and loads. Larger and heavier planes have higher landing weights. Hence, a higher landing speed is required for such planes, whereby the landing flaps are placed more steeply than with smaller and lighter planes during landing in order to achieve as high an annihilation of the lift as possible. The particularly steep arrangement of the landing flaps during the landing of the plane causes quite a large gap to be formed between the trailing edge of the spoiler and the surface of the landing flap, which gap brings about undesired aerodynamic effects.
SUMMARY OF THE INVENTION
It is the object of the present invention to provide a spoiler which is suitable for application, in particular, with large and heavy planes and offers enhanced aerodynamic conditions during the landing and take-off of a plane or the like, without adversely affecting the aerodynamic conditions during cruising. This means that the spoiler must not negatively influence the aerodynamic conditions during cruising in a higher speed range, while it is to have as small as possible a distance, or a defined distance, relative to the landing flap in the low speed range during landing. The drawbacks of known constructions are to be avoided or at least reduced. Moreover, the spoiler is to be characterized by as slight a weight as possible.
The object according to the invention is achieved in that a structural member is arranged on the trailing edge of the spoiler, viewed in the direction opposite to the flight direction, which structural member, during landing or taking off, in the unfolded state of the spoiler with the landing flaps extended reduces the gap formed between the trailing edge of the spoiler and the surface of the landing flap and which, during cruising, with the landing flap pulled in and the spoiler retracted abuts on the surface of the landing flap. Due to the extension of the trailing edge of the spoiler according to the invention, the objects of the invention are resolved by the gap formed between the trailing edge of the spoiler and the landing flap during landing or take-off in the low speed range being reduced and the aerodynamic conditions being thereby improved, while the structural member according to the invention in the higher speed range of the plane does not substantially affect the aerodynamic conditions. In addition, the extension of the trailing edge of the spoiler enhances the overlap of the spoiler with the landing flap so as to obtain a “smooth” wing.
According to a further characteristic feature of the invention, the structural member is made of a composite material and, in particular, carbon fiber reinforced plastic. This material stands out for its low weight and high mechanical properties. The use of plastics including glass fibers or aramide fibers or similar fibers may also be envisaged, yet carbon fibers exhibit the best mechanical properties.
If the structural member is composed of several layers of a fabric, a unidirectional material or a combination thereof with defined fiber orientations in each of the layers as a function of the mechanical properties of the structural member, the different spoiler properties according to the present invention will be realized. Thus, on the one hand, the required flexibility by which the structural member clings to the adjacent structural parts during cruising and, on the other hand, the desired rigidity required for preventing the structural member from being bent away during the landing flight will be obtained.
Advantageously, the cross section of the structural member is designed to taper towards the free end. Thereby, the flexibility of the free end is increased and the optimum abutment of the structural member on the wing with the lowest resistance is achieved during cruising and also the oscillating weight on the end of the structural member is reduced.
Advantages will be achieved if the free end of the structural member is designed to be curved in the direction towards the surface of the wing or the landing flap. Such a bias helps to adjust a defined gap between the spoiler and the landing flap aimed for the optimum aerodynamic conditions during the landing and take-off of the plane. Provided the appropriate flexibility of the structural member, the structural member during cruising is pressed at the landing flap against the curvature or bias with a smooth wing.
According to another characteristic feature of the invention, it is provided that the structural member is arranged substantially over the entire length of the trailing edge of the spoiler.
If the structural member is comprised of several parts, it is not necessary to replace the whole structural member in case a structural member part has been damaged.
The flexibility of the free end of the structural member may be enhanced in that the structural member on its free end comprises indents oriented substantially in the flight direction. Such inserts give rise to a substantially comb-like structural member shape optimizing the properties of the structural member.
According to a further characteristic feature, it is provided that the structural member is detachably connected with the spoiler, for instance, by means of rivet or screw connections.
Alternatively, the connection of the structural member with the spoiler may be accomplished by means of a glue connection or the like.
The characteristic features mentioned also apply if the spoiler is made in one piece with the structural member. Due to such an integrated mode of construction, mounting and dismounting of the structural member, or of the parts of the structural member, respectively, on the spoiler are omitted. However, in case of a damage to a part of the spoiler, the latter must be replaced as a whole, if need be.
In order to prevent the spoiler extension according to the invention from colliding with the landing flap, it is provided that the free end of the structural member is designed to be rounded or cambered opposite to the direction towards the surface of the wing or landing flap. As a result, the mechanical friction with the edge of the structural member is reduced during the retraction of the landing flaps, thus ensuring more gentle clinging at the landing flap located therebelow.


REFERENCES:
patent: 4712752 (1987-1

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