RU2604921C2 - Method of ice and snow removing from aircraft surface - Google Patents

Abstract

FIELD: airfield equipment.

SUBSTANCE: invention relates to aircraft surfaces servicing during preflight preparation in winter time. Method of ice and snow removing from aircraft surface consists in preparation of mixture of hot and cold air to certain temperature and following heating of critical aircraft surfaces with it. Heating of critical aircraft surfaces is performed during preflight preparation on ground through an aircraft anti-icing system by controlling ejectors gates. Snow-ice mass is removed from aircraft critical surfaces by aircraft breakaway.

EFFECT: invention simplifies preflight preparation and reduces duration of aircraft critical surfaces cleaning of ice and snow.

1 cl, 5 dwg

Description

The invention relates to the field of aviation, namely to the maintenance of aircraft surfaces during preflight preparation in the winter in accordance with the requirements of the international organization ICAO (International Civil Aviation Organization).

Modern methods of cleaning the aircraft are divided into two groups: chemical treatment of the aircraft; processing the aircraft with a stream of hot air from a device moving along the surface [1].

The main disadvantages of the above methods are the high cost of chemicals used in the processing process, the long duration of the processing process, and, as a result, during cleaning the aircraft manages to again become covered with ice and snow.

The proposed method of removing ice and snow from the surface of the aircraft can improve the quality and productivity by increasing the processing speed, mobility of the proposed device, significantly reducing the cost of the processing process.

The following analogues are considered.

A known method of cleaning the surface of an airplane from ice and snow, based on blowing the surface of a gas jet generated by a turbogenerator, which is moved along the surface to be cleaned [2].

The main disadvantages of the method are the length of the processing process and possible overheating of the skin of the aircraft with a high-temperature air stream.

An American patent is known in which the skin of an airplane is cleaned using an electromagnetic inductor installed in certain areas of the wing structure, elevator and rudder [3].

The main disadvantage of this method is the presence of heavy additional equipment on board the aircraft, which leads to an increase in the mass of the aircraft and the deterioration of technical and economic performance of the aircraft. It should also be noted the adverse effects of electromagnetic waves on the crew and maintenance personnel of the aircraft.

We also note the installation for the removal of ice from an airplane, patented in Japan [4], the main disadvantage of which is the need to build expensive objects at each airport, which preflight the aircraft, develop sophisticated ground equipment and use chemicals that have an adverse environmental impact on environment.

A known method in which the removal and prevention of icing of the aircraft is achieved by surface treatment through twin nozzles of the unit with anti-icing mixtures under excess pressure [5].

Obviously, the main disadvantages of this method are the need to develop additional equipment and the use of expensive reagents, as well as problems associated with the disposal of waste after processing the aircraft.

The closest technical solution chosen for the prototype is a method for ground cleaning of the skin of an airplane by removing ice with a gas jet taken through a fitting mounted on an airplane. Air through a flexible hose enters the nozzle [6].

The disadvantages of this method can be considered the duration of surface treatment of the aircraft, the need for additional ground equipment and personnel engaged in the maintenance of this equipment. During the processing of the aircraft, the surface manages to be covered with a new layer of ice and snow, the quality of surface treatment is sharply deteriorating.

The technical result of the invention is a significant simplification of the pre-flight preparation of the aircraft, reducing the time for cleaning critical surfaces of the aircraft from ice and snow, economic efficiency.

The technical result is achieved by the fact that the critical surfaces of the aircraft are heated with a mixture of hot and cold air previously prepared to a certain temperature. In this case, the critical surfaces of the aircraft are heated from the inside, using the existing anti-icing system. The preparation of air taken from the marching engines is carried out using ejectors installed in the air sampling system from the marching engines.

The present invention has an inventive step, novelty and industrial applicability.

The invention is illustrated by the following description and drawings, where:

in FIG. 1 shows a general view of the heated surfaces of an airplane;

in FIG. 2 shows a diagram of the heating of the slat and nose of the wing of an airplane;

in FIG. 3 shows a system for extracting hot air from marching engines and preparing air using ejectors to a predetermined temperature;

in FIG. 4 is a flow diagram of a method for removing ice and snow from an aircraft surface;

in FIG. 5 shows a diagram of the operation of the ejector.

The main heated surfaces of the aircraft processed during preflight preparation are wing slats, the front of the wing toe, keel toe and stabilizer (see Fig. 1).

Hot air enters the wing slats and nose, keel and stabilizer socks through special pipelines belonging to the aircraft de-icing system (PIC) and located in the aircraft structure (see Fig. 2).

On modern aircraft during flight during icing, it is these parts of the aircraft structure that are exposed to air-heat exposure. At the same time, the POS air-thermal system proved to be effective in operating aircraft in the most difficult climatic conditions of flight. This part of the air collectors belongs to the PIC system, which is usually activated when the aircraft is icing in flight.

The selection of hot air from the mid-flight engines of the aircraft (see. Fig. 3 and Fig. 4) are included immediately before take-off of the aircraft, located on the runway.

The hot air drawn from the marching engines has a rather high temperature (t _air ≥280 ° C). Hot air treatment at this temperature can lead to deformation of the skin of the aircraft. Therefore, for cooling the air stream in each pylon of marching engines, additional devices are installed - ejectors that perform the function of cooling the air stream to a temperature of 80-100 ° C (see Fig. 5). On each ejector, dampers are installed that regulate the selection of outdoor air necessary for cooling the hot air.

A device for implementing the proposed method comprises a hot air extraction pipe 1 from the main engine 2, blocked by a valve 3. A temperature sensor 4 is also installed in the pipe 1, which sends a signal to the control unit 5, from which, in turn, the data is displayed on the pilot panel indicator 6 The valves 7 and 8 installed in the pipeline 1 include an ejector 9 in the device’s operation. A bimetallic element 10 is installed in the ejector 9, which is hollow and has a drop-shaped cross-section, has a low temperature nertsionnostyu. The length of the bimetallic element 10 should be steamed to a predetermined temperature of 80-100 ° C (this is the temperature at which the movement is zero). At the same time, one end of it is rigidly fixed in the pipeline of increased diameter 11, and the other is movably on the rocker 12, connecting by means of the rod 13 and the lever of the axis 14 the bimetallic element 10 with the shutter 15. A temperature sensor 16 is installed at the outlet of the pipeline of increased diameter 11, which measures the temperature air entering the heated compartments 17 of the PIC system.

The essence of the method is as follows.

To remove ice and snow from critical surfaces, the aircraft rolls onto the runway. The pilot turns on the brakes on the aircraft landing gear. After warming up the marching engines, 2 engine control knobs (ORE) are set to the “nominal” mode.

Hot air from the main engine 2 enters the pipeline 1 after the valve 3 is opened. The air temperature is monitored by the temperature sensor 4. The temperature value is output to the pilot panel indicator 6 through the control unit 5. At the same time as valve 3 is opened, the ejector 9 is connected to the aircraft POS system by opening valve 7 at the inlet and valve 8 at the outlet of the ejector 9.

Hot air through the pipe 1 with temperature control by the sensor 4 enters the pipe of increased diameter 11. The incoming air heats the bimetallic element 10, which leads to the movement of the rocking chair 12 connected to the movable end of the bimetallic element 10. This causes the rod 13 to move movably connected to the axis arm 14 shutter 15, which opens the channel of external air.

Due to the ejection effect, the external cold air is sucked in, which, when it enters the pipeline of increased diameter 11, is mixed with air coming from the compressor through the pipe 1.

Mixed cooled air acts on the bimetallic element 10 and, cooling it, reduces its length, which, due to the kinematic control scheme of the shutter 15, provides rotation of the shutter 15 and partial overlap of the external air to create an air flow of a given temperature.

The temperature of the air entering the PIC of the aircraft through the ejector 9 is controlled by the installed temperature sensor 16, the values of which through the control unit 5 are displayed on the indicator of the pilot panel 6.

The temperature adjustment of the mixed air is ensured by the opening value of the controlled damper 15, through which low-temperature air enters.

Air of a given temperature ≈ 80-100 ° C enters the heated compartments 17 of the aircraft anti-icing system.

After warming up for a short time, the pilot turns off the air bleed by valve 3, turns off the valve 7 at the inlet and valve 8 at the outlet of the ejector 9, disengages the landing gear brakes, sets the marching engines 2 to cruising mode and straggles the plane from its place, which forms snowy ice mass slides from critical sections of the wing, keel, stabilizer.

The plane is ready to take off.

Thus, the present invention can significantly simplify the process and reduce the time of pre-flight preparation of the aircraft, which will significantly improve the technical and economic indicators of aircraft maintenance.

Currently, the present invention is at the design stage.

Information sources

2. A.N. Dobrokhotov, N.M. Razzhivin, V.A. Sachin. Copyright certificate No. 703953, USSR. "A method of cleaning the surface of an airplane from ice and snow."

3. Aircraft microwave defroster. US patent No. 5615849.

4. "Installation to remove ice from the aircraft." JP No. 3-70680.

5. "The method of removing and preventing icing of the aircraft and installation for its implementation." US No. 5104068.

6. "Method and device for removing ice from the surface of the aircraft." W02010075923 A1.

Claims (1)

The method of removing ice and snow from the surface of the aircraft, which consists in preparing a mixture of hot and cold air to a certain temperature using ejectors and subsequent heating of the critical surfaces of the aircraft, characterized in that the heating of critical surfaces of the aircraft is carried out during preflight preparation on the ground through the anti-icing system of the aircraft by regulation of damper of ejectors for cooling of hot air taken from marching engines, and snow-ice mass with a response These surfaces are removed by moving the aircraft from its place.

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