DE202007006212U1 - Anti-icing aircraft part - Google Patents

Abstract

Anti-icing aircraft part, characterized by an electrically conductive, an electrical resistance forming lacquer layer to the above Contact electrodes a power source is connected, for transmission a stream heating the paint layer.

Description

The The invention relates to an icing protected aircraft part, in particular the with the air in flow contact kicking and icing wings, air intakes, Propellers, as well as rotor blades and the tail rotors of helicopters.

at Aircraft moving in temperature layers with cold air and humidity, where icing may occur, There is a risk that an ice accumulation at the leading edges of wings and propellers, which negatively affects the aerodynamic profile and change it to a point can, at which the aerodynamic efficiency decreases and even lost can go. The aircraft can thereby its flying ability to lose.

Farther there is the problem that ice accumulation also air intakes the Engines can clog so that their cooling or impaired is prevented.

One Another problem is ice accumulation at the leading edge of the rotor blades of a Helicopter and its tail rotor, leading to a change in the airfoil leads. This reduces the aerodynamic efficiency to a point where the helicopter loses its ability to fly. In addition, can an ice accumulation on the rotor lead to imbalance, especially if ice in big pieces flakes off. The resulting vibrations can be exceeded the permissible Lead breaking load.

With the decreasing aerodynamic effectiveness and the decreasing Buoyancy is associated with an ice accumulation also an increase in weight, which the declining flying ability even further impaired.

A Specially feared species in aviation The icing is known as so-called "Clear Ice", which is called freezing rain impinges on the aircraft. This type of ice is like one Ice sheets stuck to the entire surface of the aircraft. The caused by the ice sheet tremendous weight gain can through conventional de-icing systems, the only the leading edges of the wing, propeller or Roteren can deice can not be effectively prevented.

So far used methods of deicing are pneumatic deicing, at the areas to be deiced be provided with a rubber mat on which the Eisansatz forms. It is partially inflated rhythmically by compressed air sections and thereby bursts the accumulated Eisbelag. Although this Method is reliable, requires the actual Use attention, as the plant is not too early and not too late actuated to be effective. Furthermore, the rubber coating be provided so that it fits smoothly into the aerodynamic profile. Also need compressed air generator and controls and compressed air lines inside the aircraft be provided. Pneumatic deicing is mainly found larger aircraft and in the upper segment of the single-engine aircraft.

Mainly at Jet aircraft is a deicing method used in the the wing leading edges be kept ice-free by heating from the inside.

This gets through in the wings running heating pipes causes, from which hot air from the inside to the outer skin is blown. This system is structurally complex and can not be retrofitted.

The De-icing by spraying of deicing fluid through a big one Number of small nozzles in the wing leading edge is also possible however, it requires consideration in the design and is so far only on smaller aircraft used and is considered the least satisfactory variant. you Use is limited in particular by the entrained amount of liquid, the for weight reasons not lush can be measured.

Farther it is already known to provide heating mats on propellers, their electricity over e.g. Obtain a slip ring and the most ice-endangered Cover the area of the propeller blade.

Especially in helicopters, their rotor blades only a very thin one and have a sensitive profile, the installation of a de-icing system applies conventional Art as technically particularly difficult.

All for blind flight approved aircraft should be in addition to the blind pilot instrumentation also over have a de-icing system, because only so can they are used largely independent of the weather, which especially in the military, but also in the emergency service and in police use strong demand becomes.

Furthermore, there is also a problem with aircraft, which are snowed or frozen during the stay on the ground, to de-ice them at the start date and de-icer, because in this state, they can not start. They must be sprayed with deicing fluid until the aircraft are ice-free. This chemical deicing agent used in this case means an environmental impact, depending but because of the air traffic because of being accepted.

According to the invention Problem of deicing of wings and fuselages now with a wing or an external component with solved the features of the main claim. The subclaims give advantageous embodiments the invention again.

Especially is advantageous that a e.g. only six microns thin paint layer which is the last one to be used for deicing purposes sprayed on the top layer of varnish can be. When energized, resistance heating forms, the e.g. can be heated up to 100 degrees.

Further Advantages and features of the invention will become apparent from the following Description of a preferred embodiment.

there is a CNT paint, a nanoparticle resistive paint, He is wear-resistant, inexpensive, easy to apply, apply everywhere, transparent and can withstand even high centrifugal forces. CNT stands for, carbon nano tubes', small carbon tubes with a few millionths of a meter in diameter. Especially through these carbon nanoparticles, can also be used in a case to be adapted lacquer layer thickness a predetermined Resistance value can be freely selected within certain limits. A typical value is the addition of a few tenths of a percent by weight of CNT flour a polymer granule base of the paint.

A power supply to the paint layer formed to the paint surfaces at their edges or even punctually in the area can contact, e.g. ensured by contact tracks which are provided up to corresponding, in the wings or components, usual (Wire) conductors, while they are on the outside the wings advantageously even against electrical contact with the environment are isolated.

It but it is also possible to coat the entire top of an airplane with a layer of varnish and to contact these at just a few points to essentially same heat conditions to achieve at the top of the paint layer. If necessary, can by skillful arrangement of the contact points of the current flow in the Near the contact points reinforced in the paint layer which makes this one higher Temperature as further away from the contact points areas have the paint layer.

Claims (4)

Anti-icing aircraft part, marked through an electrically conductive, an electrical resistance forming paint layer to the via contact electrodes a power source is connected, for the passage of a coating layer heating Current. icing Protected Aircraft part according to claim 2, characterized in that the Lackschicht a last and outer lacquer layer is. icing Protected Aircraft part according to claim 1, characterized in that the electrically conductive Paint layer formed on a plurality of insulating layers is and is covered by an insulating varnish layer. icing Protected Aircraft part according to one of claims 1-2, characterized in that the electrically conductive Lacquer layer with contact paths formed by painting electrically in contact with other power cabling and a voltage source connected is.